GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 802 A AIRFOIL (goe802a-il) Reynolds number: 1,000,000 Max Cl/Cd: 175.05 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe802a-il-1000000-n5.txt Download as CSV file: xf-goe802a-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 A 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2426 0.10228 0.10033 -0.0410 0.8838 0.0092
-9.750 -0.2356 0.09930 0.09731 -0.0424 0.8754 0.0097
-9.500 -0.2370 0.09362 0.09159 -0.0453 0.8677 0.0105
-9.250 -0.2278 0.09121 0.08917 -0.0467 0.8598 0.0106
-9.000 -0.2182 0.08893 0.08685 -0.0482 0.8522 0.0107
-8.750 -0.2081 0.08657 0.08448 -0.0499 0.8453 0.0108
-8.500 -0.1983 0.08416 0.08205 -0.0517 0.8377 0.0110
-8.250 -0.1873 0.08158 0.07943 -0.0542 0.8310 0.0112
-8.000 -0.1729 0.07864 0.07648 -0.0577 0.8239 0.0114
-7.750 -0.1572 0.07561 0.07341 -0.0614 0.8169 0.0119
-7.500 -0.1401 0.07190 0.06966 -0.0661 0.8110 0.0125
-7.250 -0.1202 0.06557 0.06328 -0.0743 0.8043 0.0133
-7.000 -0.0995 0.06315 0.06080 -0.0775 0.7971 0.0135
-6.750 -0.0776 0.06066 0.05827 -0.0808 0.7907 0.0136
-6.500 -0.0545 0.05802 0.05559 -0.0842 0.7834 0.0138
-6.250 -0.0306 0.05532 0.05280 -0.0876 0.7761 0.0141
-6.000 -0.0054 0.05252 0.04994 -0.0911 0.7690 0.0147
-5.750 0.0213 0.04916 0.04648 -0.0949 0.7604 0.0153
-5.500 0.0558 0.04277 0.03987 -0.1014 0.7525 0.0164
-5.250 0.0807 0.04069 0.03768 -0.1032 0.7396 0.0165
-5.000 0.1060 0.03900 0.03589 -0.1047 0.7248 0.0167
-4.750 0.1318 0.03732 0.03408 -0.1061 0.7101 0.0169
-4.500 0.1581 0.03572 0.03236 -0.1074 0.6973 0.0173
-4.250 0.1856 0.03373 0.03023 -0.1088 0.6843 0.0178
-4.000 0.2137 0.03149 0.02782 -0.1102 0.6709 0.0182
-3.750 0.2420 0.02931 0.02544 -0.1114 0.6570 0.0187
-3.500 0.2706 0.02713 0.02305 -0.1123 0.6437 0.0190
-3.250 0.2994 0.02499 0.02068 -0.1131 0.6312 0.0192
-3.000 0.3287 0.02241 0.01777 -0.1138 0.6181 0.0199
-2.500 0.3826 0.02044 0.01548 -0.1146 0.5878 0.0203
-2.250 0.4097 0.01972 0.01463 -0.1149 0.5747 0.0206
-2.000 0.4371 0.01895 0.01371 -0.1153 0.5630 0.0209
-1.750 0.4648 0.01810 0.01272 -0.1156 0.5523 0.0212
-1.500 0.4925 0.01725 0.01170 -0.1158 0.5422 0.0216
-1.250 0.5205 0.01635 0.01063 -0.1161 0.5317 0.0218
-1.000 0.5483 0.01546 0.00956 -0.1163 0.5216 0.0219
-0.500 0.6034 0.01168 0.00505 -0.1167 0.5035 0.0232
-0.250 0.6300 0.01099 0.00424 -0.1169 0.4953 0.0236
0.000 0.6566 0.01069 0.00386 -0.1171 0.4864 0.0238
0.250 0.6836 0.01026 0.00336 -0.1173 0.4789 0.0243
0.500 0.7107 0.01012 0.00318 -0.1174 0.4700 0.0247
0.750 0.7379 0.01001 0.00305 -0.1176 0.4622 0.0250
1.000 0.7651 0.00994 0.00296 -0.1176 0.4524 0.0253
1.250 0.7922 0.00992 0.00291 -0.1177 0.4430 0.0258
1.500 0.8193 0.00991 0.00288 -0.1178 0.4326 0.0265
1.750 0.8464 0.00993 0.00287 -0.1178 0.4229 0.0271
2.000 0.8732 0.01002 0.00291 -0.1178 0.4094 0.0276
2.250 0.8999 0.01014 0.00297 -0.1177 0.3928 0.0281
2.500 0.9263 0.01029 0.00305 -0.1177 0.3762 0.0285
2.750 0.9533 0.01048 0.00320 -0.1176 0.3648 0.0297
3.000 0.9801 0.01059 0.00330 -0.1175 0.3562 0.0309
3.250 1.0067 0.01067 0.00338 -0.1175 0.3487 0.0322
3.750 1.0598 0.01100 0.00374 -0.1174 0.3308 0.0472
4.000 1.0858 0.01109 0.00380 -0.1174 0.3214 0.0605
4.250 1.1112 0.01124 0.00391 -0.1172 0.3091 0.0642
4.500 1.1366 0.01151 0.00411 -0.1170 0.2952 0.0660
4.750 1.1628 0.01161 0.00422 -0.1169 0.2874 0.0678
5.000 1.1882 0.01178 0.00436 -0.1168 0.2793 0.0700
5.250 1.2144 0.01194 0.00453 -0.1166 0.2727 0.0734
5.500 1.2396 0.01209 0.00467 -0.1165 0.2636 0.0742
6.000 1.2891 0.01244 0.00497 -0.1160 0.2422 0.0750
6.250 1.3133 0.01267 0.00516 -0.1156 0.2278 0.0757
6.500 1.3359 0.01302 0.00543 -0.1150 0.2080 0.0761
6.750 1.3559 0.01358 0.00582 -0.1141 0.1780 0.0764
7.000 1.3761 0.01411 0.00623 -0.1131 0.1563 0.0769
7.250 1.3986 0.01443 0.00653 -0.1125 0.1458 0.0775
7.500 1.4202 0.01479 0.00686 -0.1118 0.1348 0.0780
8.000 1.4626 0.01555 0.00755 -0.1102 0.1145 0.0792
8.250 1.4827 0.01597 0.00794 -0.1092 0.1045 0.0797
8.500 1.5010 0.01649 0.00839 -0.1079 0.0913 0.0802
8.750 1.5159 0.01721 0.00899 -0.1061 0.0716 0.0813
9.250 1.5456 0.01827 0.01001 -0.1023 0.0578 0.0845
9.500 1.5595 0.01877 0.01053 -0.1002 0.0528 0.0846
9.750 1.5019 0.00858 0.00073 -0.0876 0.0505 0.0847
10.000 1.5114 0.00913 0.00130 -0.0854 0.0455 0.0851
10.250 1.5218 0.00969 0.00189 -0.0834 0.0413 0.0861
10.500 1.5219 0.01081 0.00295 -0.0802 0.0269 0.0863
10.750 1.5194 0.01222 0.00437 -0.0770 0.0154 0.0864
11.000 1.5263 0.01320 0.00541 -0.0750 0.0139 0.0865
11.250 1.5325 0.01431 0.00658 -0.0730 0.0127 0.0865
11.500 1.5385 0.01551 0.00786 -0.0711 0.0117 0.0865
11.750 1.5458 0.01671 0.00913 -0.0695 0.0113 0.0870
12.000 1.5512 0.01812 0.01062 -0.0678 0.0109 0.0874
12.250 1.5554 0.01975 0.01233 -0.0661 0.0104 0.0876
12.500 1.5581 0.02163 0.01429 -0.0644 0.0098 0.0878
12.750 1.5590 0.02377 0.01651 -0.0627 0.0094 0.0879
13.000 1.5585 0.02622 0.01904 -0.0610 0.0090 0.0879
13.250 1.5571 0.02892 0.02183 -0.0595 0.0086 0.0879
13.500 1.5567 0.03160 0.02460 -0.0581 0.0084 0.0880
14.000 1.5535 0.03775 0.03092 -0.0559 0.0081 0.0883
14.250 1.5493 0.04129 0.03456 -0.0548 0.0079 0.0885
14.500 1.5440 0.04510 0.03846 -0.0539 0.0077 0.0887
14.750 1.5378 0.04917 0.04263 -0.0531 0.0076 0.0889
15.000 1.5297 0.05350 0.04707 -0.0523 0.0074 0.0891
15.250 1.5208 0.05802 0.05169 -0.0517 0.0073 0.0892
15.500 1.5113 0.06270 0.05646 -0.0513 0.0071 0.0893
15.750 1.5001 0.06754 0.06141 -0.0509 0.0070 0.0893
16.000 1.4890 0.07240 0.06637 -0.0508 0.0069 0.0893
16.500 1.4636 0.08232 0.07649 -0.0508 0.0067 0.0894
16.750 1.4500 0.08730 0.08158 -0.0511 0.0066 0.0894
17.000 1.4352 0.09228 0.08666 -0.0514 0.0065 0.0895
17.250 1.4198 0.09725 0.09174 -0.0520 0.0064 0.0895
17.500 1.4033 0.10223 0.09683 -0.0527 0.0062 0.0896
17.750 1.3858 0.10711 0.10182 -0.0535 0.0062 0.0897
18.000 1.3681 0.11183 0.10666 -0.0544 0.0061 0.0898
18.250 1.3506 0.11614 0.11109 -0.0553 0.0061 0.0899
18.500 1.3236 0.11993 0.11501 -0.0558 0.0061 0.0899
18.750 1.3012 0.12356 0.11876 -0.0565 0.0060 0.0900
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