GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 15 AIRFOIL (goe15-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.33 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe15-il-1000000-n5.txt Download as CSV file: xf-goe15-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 15 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0154 0.09945 0.09652 -0.0887 0.7399 0.0120
-10.500 -0.0086 0.09691 0.09393 -0.0895 0.7298 0.0122
-10.000 0.0032 0.09149 0.08845 -0.0912 0.7147 0.0132
-9.750 0.0130 0.08971 0.08665 -0.0918 0.7080 0.0133
-9.500 0.0225 0.08795 0.08486 -0.0924 0.7014 0.0136
-9.250 0.0317 0.08603 0.08294 -0.0930 0.6962 0.0139
-9.000 0.0397 0.08396 0.08086 -0.0936 0.6907 0.0142
-8.500 0.0432 0.07784 0.07472 -0.0952 0.6809 0.0155
-8.250 0.0506 0.07606 0.07294 -0.0954 0.6750 0.0156
-8.000 0.0585 0.07459 0.07146 -0.0954 0.6690 0.0157
-7.750 0.0651 0.07312 0.07000 -0.0953 0.6650 0.0159
-7.500 0.0696 0.07166 0.06854 -0.0950 0.6585 0.0161
-7.250 0.0768 0.06974 0.06662 -0.0957 0.6531 0.0162
-7.000 0.0863 0.06774 0.06460 -0.0967 0.6483 0.0164
-6.750 0.0977 0.06573 0.06258 -0.0979 0.6429 0.0169
-6.500 0.1091 0.06343 0.06026 -0.0993 0.6367 0.0171
-6.250 0.1215 0.06106 0.05786 -0.1008 0.6308 0.0174
-6.000 0.1339 0.05752 0.05427 -0.1035 0.6244 0.0184
-5.750 0.1508 0.05619 0.05290 -0.1042 0.6149 0.0186
-5.500 0.1683 0.05444 0.05110 -0.1053 0.6037 0.0188
-5.250 0.1860 0.05261 0.04920 -0.1064 0.5899 0.0190
-5.000 0.2043 0.05075 0.04725 -0.1075 0.5733 0.0194
-4.750 0.2230 0.04874 0.04513 -0.1087 0.5539 0.0196
-4.500 0.2423 0.04671 0.04297 -0.1097 0.5319 0.0197
-4.250 0.2624 0.04470 0.04081 -0.1108 0.5089 0.0200
-4.000 0.2858 0.04099 0.03691 -0.1130 0.4902 0.0212
-3.750 0.3066 0.03975 0.03556 -0.1133 0.4715 0.0213
-3.500 0.3284 0.03852 0.03422 -0.1136 0.4569 0.0215
-3.000 0.3747 0.03564 0.03115 -0.1145 0.4369 0.0219
-2.750 0.3986 0.03421 0.02963 -0.1148 0.4299 0.0222
-2.500 0.4231 0.03263 0.02795 -0.1151 0.4246 0.0224
-2.250 0.4480 0.03110 0.02633 -0.1154 0.4198 0.0227
-2.000 0.4730 0.02953 0.02466 -0.1155 0.4149 0.0231
-1.500 0.5247 0.02527 0.02007 -0.1153 0.4066 0.0243
-1.250 0.5495 0.02437 0.01911 -0.1151 0.4032 0.0245
-1.000 0.5743 0.02359 0.01826 -0.1148 0.3998 0.0247
-0.750 0.5992 0.02271 0.01730 -0.1144 0.3962 0.0249
-0.500 0.6241 0.02190 0.01640 -0.1140 0.3924 0.0252
-0.250 0.6496 0.02101 0.01542 -0.1136 0.3897 0.0259
0.000 0.6755 0.01975 0.01403 -0.1130 0.3870 0.0265
0.250 0.7015 0.01772 0.01176 -0.1119 0.3844 0.0275
0.500 0.7268 0.01727 0.01125 -0.1115 0.3816 0.0277
0.750 0.7520 0.01681 0.01073 -0.1110 0.3786 0.0280
1.000 0.7770 0.01638 0.01023 -0.1104 0.3753 0.0283
1.250 0.8025 0.01590 0.00968 -0.1098 0.3726 0.0291
1.500 0.8283 0.01463 0.00822 -0.1088 0.3705 0.0304
1.750 0.8537 0.01385 0.00731 -0.1081 0.3681 0.0311
2.000 0.8792 0.01363 0.00705 -0.1076 0.3646 0.0314
2.250 0.9042 0.01341 0.00677 -0.1070 0.3603 0.0318
2.500 0.9289 0.01313 0.00641 -0.1063 0.3560 0.0326
2.750 0.9542 0.01197 0.00507 -0.1054 0.3536 0.0346
3.000 0.9797 0.01187 0.00496 -0.1050 0.3507 0.0349
3.250 1.0049 0.01178 0.00485 -0.1044 0.3471 0.0354
3.500 1.0294 0.01163 0.00466 -0.1038 0.3427 0.0361
3.750 1.0526 0.01114 0.00405 -0.1028 0.3384 0.0382
4.000 1.0774 0.01107 0.00399 -0.1022 0.3348 0.0386
4.250 1.1020 0.01110 0.00404 -0.1016 0.3313 0.0390
4.500 1.1261 0.01112 0.00405 -0.1009 0.3280 0.0396
4.750 1.1496 0.01114 0.00406 -0.1001 0.3245 0.0403
5.000 1.1733 0.01115 0.00406 -0.0993 0.3216 0.0415
5.250 1.1971 0.01115 0.00407 -0.0986 0.3188 0.0422
5.500 1.2204 0.01117 0.00409 -0.0978 0.3149 0.0429
5.750 1.2433 0.01126 0.00418 -0.0969 0.3102 0.0434
6.000 1.2657 0.01137 0.00429 -0.0959 0.3056 0.0442
6.250 1.2889 0.01145 0.00438 -0.0951 0.3018 0.0449
6.500 1.3114 0.01155 0.00450 -0.0942 0.2974 0.0462
6.750 1.3328 0.01170 0.00463 -0.0930 0.2925 0.0469
7.000 1.3541 0.01181 0.00475 -0.0919 0.2885 0.0476
7.250 1.3745 0.01192 0.00488 -0.0906 0.2837 0.0486
7.500 1.3932 0.01208 0.00504 -0.0889 0.2782 0.0494
7.750 1.4118 0.01226 0.00522 -0.0873 0.2732 0.0507
8.000 1.4307 0.01244 0.00542 -0.0857 0.2672 0.0520
8.250 1.4463 0.01278 0.00570 -0.0836 0.2552 0.0530
8.500 1.4609 0.01315 0.00602 -0.0814 0.2426 0.0545
8.750 1.4760 0.01352 0.00635 -0.0793 0.2315 0.0558
9.000 1.4897 0.01395 0.00674 -0.0770 0.2184 0.0575
9.250 1.5031 0.01441 0.00715 -0.0748 0.2068 0.0589
9.500 1.5158 0.01489 0.00760 -0.0724 0.1965 0.0621
9.750 1.5277 0.01542 0.00809 -0.0701 0.1861 0.0664
10.000 1.5396 0.01594 0.00863 -0.0677 0.1764 0.1457
10.500 1.6128 0.01656 0.01035 -0.0746 0.1532 1.0000
10.750 1.6256 0.01721 0.01097 -0.0728 0.1460 1.0000
11.000 1.6381 0.01789 0.01165 -0.0710 0.1401 1.0000
11.250 1.6512 0.01857 0.01232 -0.0693 0.1338 1.0000
11.500 1.6604 0.01950 0.01322 -0.0673 0.1248 1.0000
11.750 1.6667 0.02066 0.01431 -0.0651 0.1129 1.0000
12.000 1.6665 0.02230 0.01585 -0.0624 0.0947 1.0000
12.250 1.6635 0.02425 0.01771 -0.0598 0.0792 1.0000
12.500 1.6552 0.02674 0.02012 -0.0571 0.0611 1.0000
12.750 1.6446 0.02965 0.02296 -0.0547 0.0444 1.0000
13.000 1.6233 0.03375 0.02698 -0.0522 0.0213 1.0000
13.250 1.6190 0.03648 0.02975 -0.0509 0.0159 1.0000
13.500 1.6214 0.03862 0.03195 -0.0500 0.0145 1.0000
13.750 1.6234 0.04087 0.03426 -0.0492 0.0135 1.0000
14.000 1.6241 0.04331 0.03677 -0.0485 0.0127 1.0000
14.250 1.6236 0.04592 0.03944 -0.0478 0.0120 1.0000
14.500 1.6246 0.04844 0.04204 -0.0473 0.0116 1.0000
14.750 1.6247 0.05113 0.04480 -0.0469 0.0113 1.0000
15.000 1.6236 0.05402 0.04778 -0.0467 0.0109 1.0000
15.250 1.6208 0.05718 0.05102 -0.0465 0.0105 1.0000
15.500 1.6166 0.06061 0.05452 -0.0464 0.0102 1.0000
15.750 1.6115 0.06423 0.05822 -0.0465 0.0098 1.0000
16.000 1.6057 0.06800 0.06208 -0.0467 0.0096 1.0000
16.250 1.5977 0.07211 0.06628 -0.0471 0.0093 1.0000
16.500 1.5920 0.07597 0.07022 -0.0474 0.0091 1.0000
16.750 1.5858 0.07994 0.07428 -0.0479 0.0090 1.0000
17.000 1.5792 0.08395 0.07838 -0.0484 0.0089 1.0000
17.250 1.5720 0.08807 0.08258 -0.0490 0.0087 1.0000
17.500 1.5645 0.09224 0.08684 -0.0496 0.0086 1.0000
17.750 1.5572 0.09639 0.09108 -0.0503 0.0084 1.0000
18.000 1.5483 0.10081 0.09558 -0.0511 0.0082 1.0000
18.250 1.5407 0.10502 0.09987 -0.0519 0.0080 1.0000
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