GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 407 AIRFOIL (goe407-il) Reynolds number: 500,000 Max Cl/Cd: 95.58 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe407-il-500000-n5.txt Download as CSV file: xf-goe407-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 407 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2624 0.09212 0.08973 -0.0484 0.9879 0.0187
-8.750 -0.2605 0.08544 0.08305 -0.0565 0.9847 0.0192
-8.500 -0.2528 0.08190 0.07952 -0.0591 0.9800 0.0192
-8.250 -0.2264 0.08237 0.08000 -0.0578 0.9779 0.0204
-7.750 -0.2100 0.07526 0.07289 -0.0647 0.9662 0.0207
-7.250 -0.1894 0.06689 0.06449 -0.0743 0.9485 0.0226
-7.000 -0.1780 0.06328 0.06085 -0.0771 0.9367 0.0225
-6.750 -0.1606 0.05976 0.05728 -0.0804 0.9227 0.0220
-6.500 -0.1280 0.05001 0.04725 -0.0932 0.9008 0.0231
-6.250 -0.0837 0.04705 0.04417 -0.1005 0.8796 0.0236
-6.000 -0.0397 0.04604 0.04300 -0.1058 0.8503 0.0253
-5.750 -0.0209 0.04257 0.03924 -0.1076 0.8210 0.0253
-5.500 -0.0084 0.03929 0.03571 -0.1073 0.8021 0.0248
-5.250 0.0038 0.03602 0.03220 -0.1063 0.7877 0.0245
-5.000 0.0155 0.03248 0.02839 -0.1047 0.7751 0.0242
-4.750 0.0311 0.03039 0.02611 -0.1032 0.7631 0.0245
-4.500 0.0468 0.02818 0.02369 -0.1014 0.7513 0.0249
-4.250 0.0605 0.02534 0.02056 -0.0991 0.7388 0.0250
-4.000 0.0735 0.02231 0.01716 -0.0962 0.7258 0.0250
-3.750 0.0876 0.01973 0.01419 -0.0934 0.7118 0.0252
-3.250 0.1227 0.01625 0.00997 -0.0889 0.6836 0.0255
-3.000 0.1440 0.01532 0.00879 -0.0874 0.6719 0.0260
-2.750 0.1665 0.01456 0.00778 -0.0861 0.6629 0.0264
-2.500 0.1901 0.01382 0.00685 -0.0851 0.6551 0.0266
-2.250 0.2141 0.01326 0.00611 -0.0842 0.6481 0.0267
-2.000 0.2391 0.01278 0.00550 -0.0834 0.6412 0.0270
-1.750 0.2639 0.01241 0.00501 -0.0826 0.6345 0.0273
-1.500 0.2890 0.01209 0.00460 -0.0819 0.6282 0.0274
-1.250 0.3143 0.01184 0.00428 -0.0812 0.6218 0.0276
-0.750 0.3634 0.01108 0.00343 -0.0797 0.6090 0.0283
-0.500 0.3877 0.01085 0.00318 -0.0788 0.6021 0.0287
-0.250 0.4121 0.01067 0.00299 -0.0780 0.5958 0.0293
0.000 0.4367 0.01052 0.00284 -0.0772 0.5885 0.0299
0.250 0.4607 0.01041 0.00270 -0.0763 0.5816 0.0307
0.500 0.4854 0.01026 0.00256 -0.0755 0.5741 0.0311
0.750 0.5093 0.01018 0.00244 -0.0746 0.5666 0.0314
1.000 0.5339 0.01008 0.00235 -0.0738 0.5585 0.0320
1.250 0.5576 0.01004 0.00227 -0.0728 0.5491 0.0326
1.500 0.5817 0.01001 0.00222 -0.0719 0.5369 0.0332
1.750 0.6049 0.00998 0.00216 -0.0708 0.5227 0.0341
2.000 0.6272 0.01000 0.00212 -0.0695 0.5044 0.0356
2.250 0.6488 0.01008 0.00212 -0.0682 0.4825 0.0372
2.750 0.6892 0.01035 0.00226 -0.0649 0.4326 0.0692
3.000 0.7097 0.01051 0.00237 -0.0634 0.4119 0.0918
3.250 0.7303 0.01051 0.00252 -0.0620 0.3972 0.1854
3.750 0.9489 0.01012 0.00362 -0.0999 0.3474 1.0000
4.500 1.0148 0.01070 0.00407 -0.0964 0.3192 1.0000
4.750 1.0362 0.01091 0.00424 -0.0951 0.3114 1.0000
5.000 1.0583 0.01109 0.00441 -0.0939 0.3037 1.0000
5.250 1.0791 0.01132 0.00461 -0.0925 0.2950 1.0000
5.500 1.1002 0.01153 0.00480 -0.0912 0.2850 1.0000
5.750 1.1210 0.01175 0.00500 -0.0898 0.2787 1.0000
6.000 1.1422 0.01195 0.00520 -0.0885 0.2716 1.0000
6.250 1.1621 0.01221 0.00544 -0.0870 0.2644 1.0000
6.500 1.1826 0.01243 0.00566 -0.0856 0.2556 1.0000
6.750 1.2018 0.01270 0.00592 -0.0840 0.2482 1.0000
7.000 1.2214 0.01295 0.00617 -0.0824 0.2385 1.0000
7.250 1.2386 0.01330 0.00646 -0.0804 0.2232 1.0000
7.500 1.2545 0.01370 0.00679 -0.0782 0.2054 1.0000
7.750 1.2689 0.01417 0.00715 -0.0758 0.1832 1.0000
8.000 1.2746 0.01504 0.00774 -0.0718 0.1372 1.0000
8.250 1.2819 0.01566 0.00826 -0.0681 0.1205 1.0000
8.500 1.2928 0.01609 0.00868 -0.0649 0.1128 1.0000
8.750 1.3033 0.01656 0.00914 -0.0618 0.1064 1.0000
9.000 1.3164 0.01694 0.00955 -0.0592 0.1019 1.0000
9.250 1.3293 0.01735 0.01000 -0.0566 0.0974 1.0000
9.500 1.3405 0.01787 0.01052 -0.0538 0.0922 1.0000
9.750 1.3537 0.01830 0.01099 -0.0514 0.0877 1.0000
10.000 1.3664 0.01878 0.01149 -0.0490 0.0826 1.0000
10.250 1.3774 0.01937 0.01208 -0.0464 0.0769 1.0000
10.500 1.3894 0.01993 0.01265 -0.0440 0.0707 1.0000
10.750 1.3992 0.02062 0.01334 -0.0414 0.0633 1.0000
11.000 1.4060 0.02151 0.01417 -0.0385 0.0517 1.0000
11.250 1.4095 0.02264 0.01522 -0.0354 0.0389 1.0000
11.500 1.4066 0.02422 0.01670 -0.0317 0.0228 1.0000
11.750 1.4095 0.02553 0.01803 -0.0289 0.0186 1.0000
12.000 1.4146 0.02677 0.01934 -0.0266 0.0167 1.0000
12.250 1.4210 0.02800 0.02063 -0.0246 0.0157 1.0000
12.500 1.4255 0.02944 0.02215 -0.0226 0.0147 1.0000
12.750 1.4295 0.03100 0.02379 -0.0208 0.0139 1.0000
13.000 1.4333 0.03265 0.02552 -0.0192 0.0132 1.0000
13.250 1.4381 0.03429 0.02725 -0.0178 0.0128 1.0000
13.500 1.4424 0.03603 0.02909 -0.0166 0.0124 1.0000
13.750 1.4449 0.03799 0.03115 -0.0154 0.0119 1.0000
14.000 1.4460 0.04018 0.03342 -0.0144 0.0115 1.0000
14.250 1.4457 0.04258 0.03591 -0.0135 0.0110 1.0000
14.500 1.4435 0.04527 0.03870 -0.0127 0.0108 1.0000
14.750 1.4387 0.04836 0.04188 -0.0121 0.0104 1.0000
15.000 1.4368 0.05120 0.04483 -0.0117 0.0103 1.0000
15.250 1.4357 0.05401 0.04775 -0.0114 0.0101 1.0000
15.500 1.4321 0.05720 0.05106 -0.0113 0.0098 1.0000
15.750 1.4274 0.06063 0.05460 -0.0114 0.0097 1.0000
16.000 1.4225 0.06420 0.05828 -0.0116 0.0095 1.0000
16.250 1.4144 0.06830 0.06249 -0.0121 0.0094 1.0000
16.500 1.4077 0.07234 0.06665 -0.0128 0.0093 1.0000
16.750 1.4004 0.07659 0.07101 -0.0136 0.0091 1.0000
17.000 1.3921 0.08107 0.07559 -0.0146 0.0089 1.0000
17.250 1.3841 0.08560 0.08024 -0.0158 0.0088 1.0000
17.500 1.3737 0.09061 0.08536 -0.0171 0.0087 1.0000
17.750 1.3643 0.09551 0.09037 -0.0186 0.0086 1.0000
18.000 1.3537 0.10063 0.09559 -0.0202 0.0085 1.0000
18.250 1.3439 0.10567 0.10074 -0.0218 0.0084 1.0000
18.500 1.3335 0.11090 0.10607 -0.0236 0.0083 1.0000
18.750 1.3225 0.11629 0.11156 -0.0256 0.0083 1.0000
19.000 1.3112 0.12176 0.11712 -0.0277 0.0081 1.0000
19.250 1.3003 0.12724 0.12267 -0.0299 0.0079 1.0000
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