GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 802 A AIRFOIL (goe802a-il) Reynolds number: 500,000 Max Cl/Cd: 91.04 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe802a-il-500000-n5.txt Download as CSV file: xf-goe802a-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2082 0.10191 0.09955 -0.0473 0.9392 0.0161
-9.500 -0.2025 0.09903 0.09663 -0.0482 0.9258 0.0161
-9.250 -0.1964 0.09623 0.09380 -0.0491 0.9138 0.0160
-9.000 -0.1893 0.09346 0.09102 -0.0502 0.9047 0.0158
-8.750 -0.1824 0.09050 0.08802 -0.0517 0.8953 0.0159
-8.250 -0.1671 0.08476 0.08224 -0.0553 0.8781 0.0167
-8.000 -0.1566 0.08276 0.08020 -0.0567 0.8707 0.0174
-7.750 -0.1410 0.07961 0.07703 -0.0613 0.8627 0.0195
-7.500 -0.1251 0.07603 0.07341 -0.0659 0.8552 0.0196
-7.250 -0.1068 0.07233 0.06965 -0.0710 0.8484 0.0196
-7.000 -0.0860 0.06852 0.06578 -0.0764 0.8410 0.0197
-6.750 -0.0622 0.06448 0.06165 -0.0824 0.8342 0.0198
-6.500 -0.0465 0.06150 0.05865 -0.0838 0.8280 0.0200
-6.250 -0.0281 0.05931 0.05643 -0.0854 0.8212 0.0204
-6.000 -0.0063 0.05697 0.05402 -0.0880 0.8145 0.0211
-5.750 0.0187 0.05419 0.05118 -0.0914 0.8075 0.0224
-5.500 0.0530 0.05046 0.04729 -0.0970 0.8002 0.0236
-5.250 0.0832 0.04716 0.04382 -0.1009 0.7935 0.0237
-5.000 0.1130 0.04402 0.04052 -0.1040 0.7858 0.0238
-4.750 0.1407 0.04084 0.03715 -0.1064 0.7777 0.0239
-4.500 0.1617 0.03843 0.03471 -0.1074 0.7687 0.0242
-4.250 0.1856 0.03653 0.03269 -0.1085 0.7569 0.0245
-4.000 0.2114 0.03473 0.03078 -0.1096 0.7442 0.0249
-3.750 0.2381 0.03298 0.02888 -0.1107 0.7322 0.0257
-3.500 0.2709 0.03137 0.02699 -0.1117 0.7209 0.0282
-3.250 0.3000 0.02966 0.02503 -0.1125 0.7099 0.0284
-3.000 0.3280 0.02813 0.02326 -0.1131 0.6976 0.0285
-2.750 0.3553 0.02658 0.02151 -0.1136 0.6840 0.0285
-2.250 0.4095 0.02354 0.01807 -0.1144 0.6584 0.0285
-2.000 0.4347 0.02179 0.01625 -0.1152 0.6445 0.0275
-1.750 0.4624 0.02060 0.01484 -0.1155 0.6302 0.0271
-1.500 0.4900 0.01956 0.01358 -0.1157 0.6158 0.0271
-1.250 0.5175 0.01864 0.01243 -0.1158 0.6017 0.0270
-1.000 0.5453 0.01779 0.01138 -0.1159 0.5888 0.0275
-0.750 0.5729 0.01697 0.01035 -0.1160 0.5772 0.0278
-0.500 0.6001 0.01623 0.00943 -0.1161 0.5655 0.0274
-0.250 0.6277 0.01547 0.00851 -0.1162 0.5546 0.0273
0.000 0.6548 0.01474 0.00756 -0.1162 0.5434 0.0274
0.250 0.6821 0.01368 0.00628 -0.1162 0.5325 0.0279
0.500 0.7080 0.01259 0.00495 -0.1162 0.5226 0.0285
0.750 0.7344 0.01208 0.00435 -0.1163 0.5129 0.0291
1.000 0.7612 0.01205 0.00428 -0.1163 0.5038 0.0301
1.250 0.7880 0.01187 0.00408 -0.1164 0.4947 0.0310
1.500 0.8141 0.01170 0.00385 -0.1163 0.4857 0.0315
1.750 0.8410 0.01158 0.00373 -0.1163 0.4769 0.0321
2.250 0.8940 0.01157 0.00366 -0.1162 0.4574 0.0337
2.500 0.9203 0.01168 0.00373 -0.1161 0.4469 0.0349
2.750 0.9469 0.01177 0.00383 -0.1160 0.4351 0.0367
3.000 0.9728 0.01190 0.00393 -0.1159 0.4214 0.0393
3.250 0.9986 0.01218 0.00419 -0.1156 0.4066 0.0450
3.500 1.0243 0.01240 0.00439 -0.1154 0.3935 0.0560
3.750 1.0500 0.01259 0.00452 -0.1152 0.3833 0.0646
4.250 1.1011 0.01300 0.00487 -0.1148 0.3625 0.0732
4.500 1.1263 0.01322 0.00506 -0.1145 0.3537 0.0783
5.000 1.1765 0.01356 0.00537 -0.1140 0.3352 0.0862
5.250 1.2011 0.01371 0.00552 -0.1137 0.3237 0.0863
5.500 1.2249 0.01393 0.00569 -0.1133 0.3124 0.0864
5.750 1.2495 0.01409 0.00587 -0.1130 0.3029 0.0865
6.000 1.2732 0.01432 0.00608 -0.1126 0.2946 0.0865
6.500 1.3214 0.01462 0.00644 -0.1119 0.2781 0.0867
6.750 1.3455 0.01478 0.00664 -0.1115 0.2696 0.0869
7.000 1.3681 0.01505 0.00690 -0.1109 0.2589 0.0872
7.250 1.3909 0.01530 0.00717 -0.1104 0.2467 0.0874
7.500 1.4111 0.01575 0.00753 -0.1094 0.2261 0.0877
7.750 1.4281 0.01642 0.00804 -0.1080 0.1956 0.0878
8.000 1.4437 0.01716 0.00863 -0.1064 0.1708 0.0879
8.500 1.4795 0.01818 0.00961 -0.1038 0.1469 0.0882
8.750 1.4955 0.01872 0.01013 -0.1022 0.1368 0.0883
9.000 1.5100 0.01917 0.01060 -0.1002 0.1293 0.0886
9.250 1.5238 0.01977 0.01119 -0.0983 0.1209 0.0888
9.500 1.5392 0.02035 0.01180 -0.0967 0.1124 0.0891
9.750 1.5524 0.02110 0.01252 -0.0948 0.1023 0.0892
10.000 1.5628 0.02204 0.01339 -0.0927 0.0874 0.0893
10.250 1.5710 0.02315 0.01442 -0.0905 0.0721 0.0894
10.500 1.5807 0.02419 0.01543 -0.0885 0.0633 0.0896
10.750 1.5914 0.02519 0.01645 -0.0867 0.0583 0.0902
11.000 1.6010 0.02629 0.01757 -0.0849 0.0532 0.0906
11.250 1.6119 0.02733 0.01866 -0.0834 0.0488 0.0907
11.750 1.6182 0.03073 0.02199 -0.0792 0.0234 0.0910
12.000 1.6155 0.03304 0.02428 -0.0769 0.0170 0.0913
12.250 1.6204 0.03479 0.02612 -0.0753 0.0151 0.0916
12.500 1.6260 0.03652 0.02794 -0.0740 0.0142 0.0921
12.750 1.6302 0.03843 0.02996 -0.0727 0.0134 0.0924
13.000 1.6330 0.04055 0.03217 -0.0715 0.0128 0.0926
13.250 1.6346 0.04286 0.03458 -0.0703 0.0121 0.0931
13.500 1.6360 0.04524 0.03707 -0.0694 0.0116 0.0938
13.750 1.6387 0.04757 0.03951 -0.0686 0.0113 0.0946
14.000 1.6405 0.05009 0.04214 -0.0680 0.0109 0.0955
14.250 1.6409 0.05284 0.04500 -0.0674 0.0106 0.0963
14.500 1.6403 0.05580 0.04808 -0.0671 0.0102 0.0967
14.750 1.6388 0.05899 0.05137 -0.0669 0.0099 0.0972
15.000 1.6358 0.06243 0.05492 -0.0668 0.0097 0.0980
15.250 1.6314 0.06613 0.05875 -0.0669 0.0094 0.0989
15.500 1.6256 0.07013 0.06287 -0.0671 0.0092 0.0993
15.750 1.6181 0.07445 0.06731 -0.0676 0.0090 0.1001
16.000 1.6089 0.07907 0.07206 -0.0682 0.0089 0.1012
16.250 1.5971 0.08418 0.07731 -0.0690 0.0087 0.1018
16.500 1.5880 0.08898 0.08222 -0.0699 0.0086 0.1028
16.750 1.5800 0.09367 0.08703 -0.0709 0.0085 0.1042
17.000 1.5713 0.09851 0.09198 -0.0720 0.0084 0.1057
17.250 1.5620 0.10353 0.09713 -0.0733 0.0083 0.1078
17.500 1.5520 0.10873 0.10244 -0.0748 0.0082 0.1103
17.750 1.5419 0.11402 0.10784 -0.0764 0.0081 0.1121
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