GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.11 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe704-il-1000000.txt Download as CSV file: xf-goe704-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 704 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0772 0.08830 0.08555 -0.0151 1.0000 0.0102
-16.250 -1.1384 0.07459 0.07168 -0.0227 1.0000 0.0100
-16.000 -1.2316 0.05018 0.04685 -0.0413 1.0000 0.0096
-15.750 -1.2590 0.04184 0.03825 -0.0474 1.0000 0.0096
-15.500 -1.2702 0.03817 0.03442 -0.0475 1.0000 0.0097
-15.250 -1.2764 0.03550 0.03163 -0.0463 1.0000 0.0098
-15.000 -1.2788 0.03340 0.02941 -0.0445 1.0000 0.0099
-14.750 -1.2787 0.03163 0.02754 -0.0423 1.0000 0.0100
-14.500 -1.2761 0.03013 0.02593 -0.0399 1.0000 0.0102
-14.250 -1.2721 0.02880 0.02449 -0.0373 1.0000 0.0103
-14.000 -1.2664 0.02764 0.02323 -0.0346 1.0000 0.0105
-13.750 -1.2588 0.02662 0.02211 -0.0319 1.0000 0.0107
-13.500 -1.2464 0.02565 0.02105 -0.0300 1.0000 0.0109
-13.250 -1.2315 0.02478 0.02009 -0.0284 1.0000 0.0110
-13.000 -1.2145 0.02401 0.01923 -0.0270 1.0000 0.0112
-12.750 -1.2065 0.02246 0.01754 -0.0245 1.0000 0.0116
-12.500 -1.1913 0.02141 0.01641 -0.0228 1.0000 0.0120
-12.250 -1.1727 0.02061 0.01554 -0.0216 1.0000 0.0123
-12.000 -1.1525 0.01992 0.01479 -0.0206 1.0000 0.0127
-11.750 -1.1316 0.01927 0.01408 -0.0196 1.0000 0.0131
-11.500 -1.1101 0.01865 0.01340 -0.0187 1.0000 0.0135
-11.250 -1.0876 0.01811 0.01280 -0.0179 1.0000 0.0139
-11.000 -1.0668 0.01738 0.01198 -0.0169 1.0000 0.0145
-10.750 -1.0458 0.01664 0.01119 -0.0159 1.0000 0.0153
-10.500 -1.0228 0.01612 0.01065 -0.0152 1.0000 0.0160
-10.250 -0.9997 0.01566 0.01014 -0.0145 1.0000 0.0167
-10.000 -0.9675 0.01521 0.00963 -0.0156 0.9902 0.0174
-9.750 -0.9382 0.01447 0.00885 -0.0163 0.9763 0.0191
-9.500 -0.9115 0.01405 0.00838 -0.0161 0.9581 0.0204
-9.250 -0.8893 0.01368 0.00794 -0.0149 0.9373 0.0219
-9.000 -0.8674 0.01326 0.00747 -0.0136 0.9166 0.0244
-8.750 -0.8442 0.01291 0.00703 -0.0126 0.8975 0.0273
-8.500 -0.8200 0.01257 0.00665 -0.0118 0.8800 0.0310
-8.250 -0.7955 0.01220 0.00623 -0.0112 0.8639 0.0357
-8.000 -0.7701 0.01189 0.00587 -0.0107 0.8493 0.0404
-7.750 -0.7442 0.01163 0.00557 -0.0103 0.8365 0.0449
-7.500 -0.7184 0.01131 0.00522 -0.0099 0.8252 0.0509
-7.250 -0.6920 0.01104 0.00493 -0.0096 0.8147 0.0571
-7.000 -0.6654 0.01079 0.00467 -0.0093 0.8056 0.0640
-6.750 -0.6388 0.01054 0.00442 -0.0091 0.7972 0.0729
-6.500 -0.6117 0.01032 0.00423 -0.0090 0.7899 0.0819
-6.250 -0.5842 0.01016 0.00406 -0.0089 0.7828 0.0892
-6.000 -0.5566 0.01004 0.00393 -0.0088 0.7765 0.0959
-5.750 -0.5285 0.00991 0.00378 -0.0088 0.7705 0.1005
-5.500 -0.5008 0.00979 0.00365 -0.0087 0.7648 0.1064
-5.250 -0.4723 0.00974 0.00357 -0.0088 0.7596 0.1108
-5.000 -0.4445 0.00959 0.00341 -0.0088 0.7544 0.1159
-4.750 -0.4165 0.00948 0.00329 -0.0087 0.7494 0.1200
-4.500 -0.3882 0.00940 0.00318 -0.0088 0.7446 0.1232
-4.250 -0.3595 0.00934 0.00309 -0.0089 0.7400 0.1254
-4.000 -0.3318 0.00917 0.00291 -0.0088 0.7351 0.1301
-3.750 -0.3038 0.00908 0.00281 -0.0088 0.7301 0.1343
-3.500 -0.2753 0.00898 0.00270 -0.0088 0.7243 0.1379
-3.250 -0.2468 0.00893 0.00260 -0.0089 0.7168 0.1403
-3.000 -0.2190 0.00877 0.00245 -0.0088 0.7101 0.1464
-2.750 -0.1907 0.00866 0.00236 -0.0089 0.7047 0.1518
-2.500 -0.1622 0.00861 0.00227 -0.0089 0.6999 0.1555
-2.250 -0.1341 0.00848 0.00216 -0.0089 0.6952 0.1629
-2.000 -0.1056 0.00836 0.00207 -0.0090 0.6903 0.1694
-1.750 -0.0775 0.00825 0.00198 -0.0090 0.6852 0.1797
-1.500 -0.0494 0.00814 0.00191 -0.0090 0.6803 0.1945
-1.250 -0.0214 0.00796 0.00184 -0.0091 0.6749 0.2195
-1.000 0.0061 0.00778 0.00178 -0.0090 0.6693 0.2557
-0.750 0.0337 0.00763 0.00173 -0.0090 0.6627 0.2907
-0.500 0.0615 0.00747 0.00168 -0.0089 0.6542 0.3246
-0.250 0.0890 0.00732 0.00163 -0.0089 0.6456 0.3637
0.000 0.1157 0.00708 0.00158 -0.0087 0.6374 0.4221
0.250 0.1400 0.00664 0.00152 -0.0081 0.6305 0.5378
0.500 0.1511 0.00548 0.00152 -0.0044 0.6233 0.8667
0.750 0.1783 0.00552 0.00160 -0.0040 0.6151 0.8968
1.000 0.2059 0.00558 0.00165 -0.0037 0.6053 0.9120
1.250 0.2334 0.00566 0.00170 -0.0034 0.5946 0.9232
1.500 0.2611 0.00576 0.00177 -0.0032 0.5802 0.9307
1.750 0.2877 0.00589 0.00182 -0.0028 0.5602 0.9382
2.000 0.3147 0.00605 0.00191 -0.0024 0.5369 0.9441
2.250 0.3412 0.00624 0.00201 -0.0019 0.5130 0.9503
2.500 0.3668 0.00644 0.00210 -0.0014 0.4867 0.9555
2.750 0.3949 0.00670 0.00226 -0.0013 0.4576 0.9598
3.000 0.4227 0.00700 0.00243 -0.0013 0.4289 0.9651
3.250 0.4483 0.00725 0.00258 -0.0007 0.4030 0.9700
3.500 0.4842 0.00755 0.00277 -0.0025 0.3782 0.9722
4.000 0.5637 0.00822 0.00322 -0.0080 0.3313 0.9756
4.250 0.5988 0.00847 0.00340 -0.0097 0.3133 0.9773
4.500 0.6300 0.00868 0.00354 -0.0106 0.2989 0.9794
4.750 0.6551 0.00888 0.00369 -0.0101 0.2868 0.9825
5.000 0.6922 0.00909 0.00384 -0.0123 0.2730 0.9832
5.250 0.7261 0.00929 0.00398 -0.0138 0.2595 0.9839
5.500 0.7568 0.00946 0.00411 -0.0147 0.2473 0.9844
5.750 0.7871 0.00962 0.00424 -0.0154 0.2369 0.9850
6.000 0.8169 0.00981 0.00439 -0.0161 0.2269 0.9857
6.500 0.8757 0.01022 0.00471 -0.0173 0.2052 0.9872
6.750 0.9047 0.01042 0.00489 -0.0179 0.1965 0.9881
7.000 0.9332 0.01066 0.00508 -0.0183 0.1872 0.9891
7.250 0.9620 0.01085 0.00527 -0.0188 0.1800 0.9902
7.500 0.9896 0.01111 0.00549 -0.0191 0.1713 0.9915
7.750 1.0167 0.01131 0.00569 -0.0192 0.1638 0.9928
8.000 1.0432 0.01159 0.00593 -0.0193 0.1546 0.9938
8.250 1.0723 0.01190 0.00619 -0.0200 0.1418 0.9943
8.500 1.0997 0.01237 0.00653 -0.0205 0.1176 0.9950
8.750 1.1248 0.01308 0.00705 -0.0208 0.0904 0.9959
9.000 1.1514 0.01358 0.00749 -0.0211 0.0817 0.9967
9.250 1.1789 0.01394 0.00787 -0.0216 0.0757 0.9976
9.500 1.2050 0.01444 0.00834 -0.0218 0.0668 0.9986
9.750 1.2227 0.01582 0.00939 -0.0212 0.0266 0.9998
10.000 1.2356 0.01651 0.01006 -0.0189 0.0204 1.0000
10.250 1.2454 0.01702 0.01059 -0.0159 0.0183 1.0000
10.500 1.2545 0.01746 0.01106 -0.0127 0.0172 1.0000
10.750 1.2596 0.01795 0.01158 -0.0088 0.0163 1.0000
11.000 1.2599 0.01849 0.01217 -0.0040 0.0154 1.0000
11.250 1.2536 0.01891 0.01264 0.0021 0.0150 1.0000
11.500 1.2582 0.01943 0.01321 0.0057 0.0146 1.0000
11.750 1.2677 0.02011 0.01395 0.0081 0.0141 1.0000
12.000 1.2786 0.02091 0.01479 0.0099 0.0135 1.0000
12.250 1.2889 0.02185 0.01578 0.0116 0.0130 1.0000
12.500 1.2964 0.02309 0.01708 0.0133 0.0124 1.0000
12.750 1.3022 0.02456 0.01864 0.0149 0.0120 1.0000
13.000 1.3138 0.02567 0.01981 0.0158 0.0117 1.0000
13.250 1.3238 0.02695 0.02115 0.0167 0.0114 1.0000
13.500 1.3326 0.02839 0.02267 0.0176 0.0111 1.0000
13.750 1.3405 0.02996 0.02431 0.0183 0.0109 1.0000
14.000 1.3470 0.03169 0.02610 0.0189 0.0106 1.0000
14.250 1.3525 0.03359 0.02807 0.0195 0.0104 1.0000
14.500 1.3557 0.03574 0.03030 0.0199 0.0102 1.0000
14.750 1.3560 0.03824 0.03288 0.0203 0.0100 1.0000
15.000 1.3519 0.04128 0.03601 0.0205 0.0098 1.0000
15.250 1.3417 0.04506 0.03992 0.0206 0.0096 1.0000
15.500 1.3274 0.04955 0.04453 0.0202 0.0094 1.0000
15.750 1.3268 0.05264 0.04772 0.0197 0.0093 1.0000
16.000 1.3242 0.05610 0.05127 0.0190 0.0093 1.0000
16.250 1.3196 0.05995 0.05523 0.0180 0.0092 1.0000
16.500 1.3134 0.06418 0.05955 0.0168 0.0091 1.0000
16.750 1.3060 0.06865 0.06413 0.0154 0.0090 1.0000
17.000 1.2966 0.07356 0.06915 0.0137 0.0089 1.0000
17.250 1.2861 0.07873 0.07443 0.0118 0.0089 1.0000
17.500 1.2750 0.08404 0.07984 0.0099 0.0088 1.0000
17.750 1.2633 0.08952 0.08542 0.0078 0.0087 1.0000
18.000 1.2514 0.09508 0.09109 0.0056 0.0086 1.0000
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