GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 617 AIRFOIL (goe617-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.33 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe617-il-1000000-n5.txt Download as CSV file: xf-goe617-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 617 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.9574 0.10686 0.10423 -0.0431 1.0000 0.0118
-18.750 -1.1183 0.07551 0.07238 -0.0614 1.0000 0.0108
-18.500 -1.1792 0.06162 0.05821 -0.0702 1.0000 0.0106
-18.250 -1.2120 0.05306 0.04945 -0.0757 1.0000 0.0106
-18.000 -1.2313 0.04710 0.04333 -0.0792 1.0000 0.0106
-17.750 -1.2438 0.04260 0.03869 -0.0813 1.0000 0.0107
-17.500 -1.2520 0.03903 0.03500 -0.0824 1.0000 0.0108
-17.250 -1.2582 0.03604 0.03191 -0.0827 1.0000 0.0111
-17.000 -1.2614 0.03362 0.02939 -0.0823 1.0000 0.0114
-16.750 -1.2620 0.03164 0.02732 -0.0814 1.0000 0.0116
-16.500 -1.2604 0.02999 0.02559 -0.0801 1.0000 0.0119
-16.250 -1.2576 0.02854 0.02406 -0.0785 1.0000 0.0122
-16.000 -1.2539 0.02727 0.02271 -0.0767 1.0000 0.0126
-15.750 -1.2488 0.02617 0.02153 -0.0746 1.0000 0.0127
-15.500 -1.2429 0.02520 0.02048 -0.0725 1.0000 0.0130
-15.250 -1.2365 0.02432 0.01953 -0.0701 1.0000 0.0132
-15.000 -1.2311 0.02344 0.01860 -0.0674 1.0000 0.0137
-14.750 -1.2247 0.02269 0.01781 -0.0645 1.0000 0.0142
-14.500 -1.2178 0.02205 0.01712 -0.0616 1.0000 0.0146
-14.250 -1.2112 0.02147 0.01650 -0.0584 1.0000 0.0151
-14.000 -1.2055 0.02096 0.01594 -0.0549 1.0000 0.0155
-13.750 -1.2015 0.02052 0.01544 -0.0508 1.0000 0.0159
-13.500 -1.1891 0.02004 0.01491 -0.0485 0.9995 0.0164
-13.250 -1.1633 0.01942 0.01426 -0.0489 0.9978 0.0171
-13.000 -1.1371 0.01887 0.01368 -0.0492 0.9954 0.0179
-12.750 -1.1121 0.01834 0.01312 -0.0492 0.9925 0.0186
-12.500 -1.0867 0.01784 0.01257 -0.0492 0.9894 0.0192
-12.250 -1.0594 0.01737 0.01204 -0.0496 0.9865 0.0197
-12.000 -1.0315 0.01682 0.01147 -0.0502 0.9840 0.0205
-11.750 -1.0071 0.01637 0.01100 -0.0499 0.9797 0.0213
-11.500 -0.9808 0.01595 0.01055 -0.0499 0.9754 0.0220
-11.000 -0.9247 0.01515 0.00967 -0.0506 0.9670 0.0232
-10.750 -0.8924 0.01474 0.00921 -0.0519 0.9617 0.0239
-10.500 -0.8554 0.01419 0.00863 -0.0543 0.9571 0.0247
-10.250 -0.8182 0.01374 0.00816 -0.0566 0.9496 0.0256
-9.750 -0.7455 0.01297 0.00730 -0.0608 0.9346 0.0272
-9.500 -0.7118 0.01266 0.00692 -0.0622 0.9255 0.0279
-9.250 -0.6834 0.01235 0.00655 -0.0625 0.9147 0.0286
-9.000 -0.6586 0.01204 0.00620 -0.0621 0.9048 0.0296
-8.500 -0.6112 0.01155 0.00562 -0.0605 0.8859 0.0313
-8.250 -0.5877 0.01135 0.00536 -0.0597 0.8775 0.0322
-8.000 -0.5646 0.01114 0.00511 -0.0587 0.8696 0.0328
-7.500 -0.5186 0.01072 0.00461 -0.0567 0.8540 0.0351
-7.250 -0.4954 0.01053 0.00439 -0.0557 0.8460 0.0364
-7.000 -0.4718 0.01035 0.00418 -0.0548 0.8385 0.0377
-6.750 -0.4482 0.01019 0.00398 -0.0539 0.8305 0.0391
-6.500 -0.4246 0.01000 0.00378 -0.0530 0.8230 0.0417
-6.250 -0.4009 0.00985 0.00361 -0.0521 0.8145 0.0445
-6.000 -0.3768 0.00970 0.00344 -0.0513 0.8067 0.0473
-5.750 -0.3529 0.00956 0.00330 -0.0504 0.7973 0.0512
-5.500 -0.3283 0.00945 0.00316 -0.0496 0.7889 0.0540
-5.250 -0.3043 0.00933 0.00303 -0.0488 0.7794 0.0577
-5.000 -0.2796 0.00923 0.00291 -0.0480 0.7690 0.0605
-4.750 -0.2551 0.00916 0.00280 -0.0473 0.7580 0.0624
-4.500 -0.2311 0.00908 0.00266 -0.0463 0.7453 0.0648
-4.250 -0.2070 0.00898 0.00255 -0.0455 0.7315 0.0677
-4.000 -0.1833 0.00893 0.00244 -0.0445 0.7147 0.0700
-3.750 -0.1599 0.00892 0.00234 -0.0435 0.6941 0.0718
-3.500 -0.1364 0.00892 0.00225 -0.0425 0.6725 0.0729
-3.250 -0.1127 0.00890 0.00216 -0.0415 0.6542 0.0744
-3.000 -0.0887 0.00885 0.00206 -0.0406 0.6395 0.0771
-2.750 -0.0646 0.00880 0.00198 -0.0398 0.6263 0.0801
-2.500 -0.0402 0.00876 0.00191 -0.0390 0.6146 0.0839
-2.250 -0.0153 0.00870 0.00183 -0.0383 0.6041 0.0892
-2.000 0.0090 0.00865 0.00177 -0.0375 0.5931 0.0956
-1.750 0.0319 0.00848 0.00169 -0.0365 0.5826 0.1272
-1.500 0.0554 0.00833 0.00165 -0.0356 0.5740 0.1637
-1.250 0.0799 0.00827 0.00162 -0.0348 0.5648 0.1819
-1.000 0.1045 0.00821 0.00158 -0.0341 0.5551 0.1997
-0.750 0.1285 0.00819 0.00155 -0.0332 0.5415 0.2139
-0.500 0.1522 0.00816 0.00153 -0.0323 0.5285 0.2327
-0.250 0.1710 0.00777 0.00146 -0.0306 0.5181 0.3370
0.000 0.1933 0.00762 0.00145 -0.0294 0.5105 0.3915
0.250 0.2166 0.00750 0.00145 -0.0285 0.5025 0.4309
0.500 0.2394 0.00741 0.00145 -0.0274 0.4948 0.4702
0.750 0.2608 0.00725 0.00145 -0.0260 0.4857 0.5250
1.000 0.2818 0.00714 0.00146 -0.0245 0.4752 0.5759
1.250 0.2999 0.00697 0.00147 -0.0224 0.4640 0.6445
1.500 0.3177 0.00679 0.00149 -0.0202 0.4537 0.7101
1.750 0.3358 0.00668 0.00153 -0.0180 0.4430 0.7644
2.000 0.3554 0.00662 0.00159 -0.0161 0.4324 0.8126
2.250 0.3781 0.00660 0.00168 -0.0149 0.4227 0.8547
2.500 0.4039 0.00666 0.00178 -0.0143 0.4126 0.8815
2.750 0.4311 0.00676 0.00187 -0.0142 0.4007 0.8975
3.000 0.4575 0.00690 0.00197 -0.0138 0.3848 0.9096
3.250 0.4885 0.00708 0.00211 -0.0146 0.3677 0.9219
3.500 0.5191 0.00730 0.00225 -0.0153 0.3488 0.9310
3.750 0.5494 0.00753 0.00241 -0.0159 0.3295 0.9407
4.000 0.5857 0.00777 0.00259 -0.0179 0.3143 0.9474
4.250 0.6148 0.00800 0.00277 -0.0182 0.3004 0.9562
4.500 0.6504 0.00831 0.00298 -0.0201 0.2773 0.9600
4.750 0.6839 0.00868 0.00322 -0.0216 0.2515 0.9636
5.000 0.7088 0.00909 0.00348 -0.0212 0.2184 0.9685
5.250 0.7322 0.00964 0.00382 -0.0206 0.1789 0.9722
5.500 0.7626 0.00997 0.00407 -0.0215 0.1644 0.9735
5.750 0.7925 0.01021 0.00428 -0.0221 0.1571 0.9749
6.000 0.8210 0.01047 0.00450 -0.0225 0.1498 0.9766
6.250 0.8492 0.01065 0.00469 -0.0228 0.1456 0.9786
6.500 0.8733 0.01089 0.00490 -0.0222 0.1399 0.9817
6.750 0.8997 0.01114 0.00513 -0.0222 0.1328 0.9836
7.000 0.9296 0.01139 0.00536 -0.0229 0.1258 0.9846
7.250 0.9585 0.01168 0.00561 -0.0235 0.1179 0.9859
7.500 0.9861 0.01199 0.00587 -0.0239 0.1086 0.9874
7.750 1.0127 0.01230 0.00615 -0.0240 0.1000 0.9891
8.000 1.0382 0.01264 0.00645 -0.0239 0.0928 0.9912
8.250 1.0625 0.01296 0.00675 -0.0236 0.0881 0.9933
8.500 1.0887 0.01332 0.00707 -0.0237 0.0816 0.9948
8.750 1.1148 0.01364 0.00739 -0.0239 0.0772 0.9964
9.000 1.1397 0.01401 0.00773 -0.0239 0.0725 0.9981
9.250 1.1663 0.01430 0.00804 -0.0241 0.0701 0.9993
9.500 1.1858 0.01458 0.00833 -0.0229 0.0679 1.0000
9.750 1.1914 0.01483 0.00860 -0.0188 0.0658 1.0000
10.000 1.1984 0.01514 0.00891 -0.0150 0.0638 1.0000
10.250 1.2068 0.01548 0.00927 -0.0116 0.0616 1.0000
10.500 1.2178 0.01580 0.00961 -0.0088 0.0604 1.0000
10.750 1.2293 0.01616 0.00999 -0.0062 0.0585 1.0000
11.000 1.2405 0.01657 0.01043 -0.0036 0.0566 1.0000
11.250 1.2519 0.01702 0.01089 -0.0011 0.0551 1.0000
11.500 1.2620 0.01757 0.01144 0.0014 0.0524 1.0000
11.750 1.2746 0.01805 0.01195 0.0034 0.0510 1.0000
12.000 1.2868 0.01859 0.01252 0.0055 0.0492 1.0000
12.250 1.2979 0.01923 0.01318 0.0075 0.0467 1.0000
12.500 1.3080 0.01996 0.01392 0.0095 0.0442 1.0000
12.750 1.3193 0.02067 0.01465 0.0113 0.0411 1.0000
13.000 1.3278 0.02160 0.01557 0.0133 0.0372 1.0000
13.250 1.3339 0.02272 0.01666 0.0153 0.0308 1.0000
13.500 1.3324 0.02441 0.01829 0.0178 0.0209 1.0000
13.750 1.3364 0.02583 0.01974 0.0196 0.0176 1.0000
14.000 1.3404 0.02733 0.02127 0.0212 0.0153 1.0000
14.250 1.3465 0.02874 0.02272 0.0225 0.0141 1.0000
14.500 1.3518 0.03027 0.02431 0.0237 0.0132 1.0000
14.750 1.3574 0.03185 0.02593 0.0247 0.0125 1.0000
15.000 1.3632 0.03347 0.02762 0.0256 0.0119 1.0000
15.250 1.3686 0.03518 0.02939 0.0263 0.0115 1.0000
15.500 1.3724 0.03711 0.03138 0.0270 0.0110 1.0000
15.750 1.3757 0.03914 0.03347 0.0275 0.0106 1.0000
16.000 1.3770 0.04147 0.03587 0.0279 0.0101 1.0000
16.250 1.3804 0.04365 0.03812 0.0281 0.0098 1.0000
16.500 1.3830 0.04595 0.04050 0.0282 0.0095 1.0000
16.750 1.3845 0.04845 0.04307 0.0281 0.0093 1.0000
17.000 1.3850 0.05111 0.04581 0.0280 0.0092 1.0000
17.250 1.3836 0.05406 0.04884 0.0277 0.0088 1.0000
17.500 1.3817 0.05711 0.05197 0.0273 0.0086 1.0000
17.750 1.3796 0.06026 0.05519 0.0268 0.0085 1.0000
18.000 1.3759 0.06369 0.05870 0.0261 0.0083 1.0000
18.250 1.3699 0.06746 0.06256 0.0252 0.0081 1.0000
18.500 1.3631 0.07140 0.06659 0.0242 0.0080 1.0000
18.750 1.3556 0.07554 0.07082 0.0230 0.0078 1.0000
19.000 1.3504 0.07945 0.07483 0.0218 0.0077 1.0000
19.250 1.3420 0.08386 0.07933 0.0204 0.0076 1.0000
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