GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 797 AIRFOIL (goe797-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.68 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe797-il-1000000.txt Download as CSV file: xf-goe797-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 797 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7316 0.10747 0.10509 -0.0683 1.0000 0.0298
-17.250 -0.8013 0.09197 0.08940 -0.0777 1.0000 0.0301
-17.000 -0.8542 0.08035 0.07762 -0.0851 1.0000 0.0302
-16.750 -0.9104 0.06857 0.06568 -0.0928 1.0000 0.0302
-16.500 -0.9616 0.05747 0.05440 -0.1003 1.0000 0.0302
-16.250 -1.0017 0.04723 0.04397 -0.1082 1.0000 0.0302
-16.000 -1.0314 0.03947 0.03604 -0.1144 1.0000 0.0302
-15.750 -1.0526 0.03481 0.03123 -0.1171 0.9987 0.0303
-15.500 -1.0427 0.03166 0.02797 -0.1213 0.9956 0.0306
-15.250 -1.0280 0.02950 0.02571 -0.1240 0.9934 0.0308
-15.000 -1.0135 0.02789 0.02401 -0.1251 0.9898 0.0311
-14.750 -0.9973 0.02658 0.02262 -0.1255 0.9853 0.0313
-14.500 -0.9778 0.02543 0.02139 -0.1260 0.9818 0.0316
-14.250 -0.9620 0.02448 0.02035 -0.1254 0.9757 0.0320
-14.000 -0.9447 0.02358 0.01937 -0.1247 0.9703 0.0323
-13.750 -0.9270 0.02282 0.01851 -0.1239 0.9650 0.0326
-13.500 -0.9093 0.02213 0.01773 -0.1228 0.9589 0.0329
-13.250 -0.8901 0.02152 0.01703 -0.1218 0.9537 0.0332
-13.000 -0.8700 0.02095 0.01637 -0.1210 0.9480 0.0334
-12.750 -0.8543 0.01991 0.01522 -0.1197 0.9419 0.0338
-12.500 -0.8363 0.01903 0.01427 -0.1186 0.9366 0.0343
-12.250 -0.8147 0.01840 0.01360 -0.1180 0.9312 0.0347
-12.000 -0.7922 0.01788 0.01303 -0.1173 0.9255 0.0351
-11.750 -0.7689 0.01742 0.01250 -0.1168 0.9201 0.0356
-11.500 -0.7447 0.01695 0.01198 -0.1164 0.9143 0.0360
-11.250 -0.7204 0.01651 0.01147 -0.1159 0.9083 0.0365
-11.000 -0.6956 0.01611 0.01099 -0.1155 0.9027 0.0371
-10.750 -0.6697 0.01574 0.01056 -0.1153 0.8964 0.0375
-10.500 -0.6438 0.01544 0.01017 -0.1150 0.8897 0.0379
-10.250 -0.6206 0.01472 0.00938 -0.1145 0.8828 0.0387
-10.000 -0.5953 0.01425 0.00888 -0.1142 0.8748 0.0394
-9.750 -0.5691 0.01391 0.00848 -0.1140 0.8672 0.0401
-9.500 -0.5423 0.01360 0.00812 -0.1139 0.8583 0.0408
-9.250 -0.5156 0.01331 0.00776 -0.1137 0.8495 0.0415
-9.000 -0.4884 0.01304 0.00742 -0.1136 0.8391 0.0422
-8.750 -0.4610 0.01282 0.00712 -0.1135 0.8284 0.0428
-8.500 -0.4354 0.01237 0.00658 -0.1132 0.8164 0.0440
-8.250 -0.4082 0.01209 0.00627 -0.1132 0.8041 0.0451
-8.000 -0.3805 0.01190 0.00601 -0.1131 0.7931 0.0462
-7.500 -0.3247 0.01157 0.00553 -0.1131 0.7732 0.0482
-7.000 -0.2696 0.01103 0.00491 -0.1131 0.7569 0.0515
-6.750 -0.2414 0.01089 0.00470 -0.1132 0.7495 0.0530
-6.500 -0.2127 0.01077 0.00453 -0.1133 0.7435 0.0542
-6.250 -0.1847 0.01049 0.00424 -0.1134 0.7379 0.0567
-6.000 -0.1563 0.01035 0.00407 -0.1135 0.7324 0.0589
-5.750 -0.1275 0.01026 0.00393 -0.1137 0.7272 0.0607
-5.500 -0.0989 0.01002 0.00370 -0.1138 0.7227 0.0639
-5.250 -0.0700 0.00989 0.00356 -0.1140 0.7180 0.0667
-5.000 -0.0414 0.00977 0.00340 -0.1142 0.7132 0.0699
-4.750 -0.0126 0.00963 0.00327 -0.1144 0.7083 0.0739
-4.500 0.0165 0.00950 0.00314 -0.1146 0.7036 0.0783
-4.250 0.0454 0.00939 0.00304 -0.1148 0.6985 0.0835
-4.000 0.0741 0.00931 0.00294 -0.1149 0.6935 0.0892
-3.750 0.1034 0.00923 0.00287 -0.1152 0.6898 0.0947
-3.500 0.1327 0.00911 0.00280 -0.1155 0.6858 0.1015
-3.250 0.1620 0.00907 0.00274 -0.1157 0.6811 0.1064
-3.000 0.1908 0.00901 0.00269 -0.1159 0.6764 0.1130
-2.750 0.2202 0.00899 0.00265 -0.1162 0.6726 0.1177
-2.500 0.2496 0.00889 0.00259 -0.1165 0.6689 0.1233
-2.250 0.2789 0.00884 0.00255 -0.1167 0.6644 0.1285
-2.000 0.3080 0.00885 0.00252 -0.1169 0.6596 0.1320
-1.750 0.3370 0.00878 0.00246 -0.1172 0.6547 0.1377
-1.500 0.3664 0.00871 0.00242 -0.1175 0.6503 0.1430
-1.250 0.3958 0.00870 0.00239 -0.1177 0.6461 0.1466
-1.000 0.4247 0.00865 0.00234 -0.1179 0.6421 0.1524
-0.750 0.4536 0.00863 0.00232 -0.1182 0.6380 0.1585
-0.500 0.4832 0.00858 0.00230 -0.1185 0.6346 0.1633
-0.250 0.5124 0.00851 0.00227 -0.1188 0.6305 0.1725
0.000 0.5414 0.00848 0.00225 -0.1190 0.6262 0.1814
0.250 0.5698 0.00845 0.00225 -0.1192 0.6215 0.1987
0.500 0.5988 0.00831 0.00225 -0.1195 0.6175 0.2358
0.750 0.6274 0.00815 0.00227 -0.1198 0.6125 0.2962
1.000 0.6555 0.00798 0.00229 -0.1200 0.6073 0.3669
1.250 0.6828 0.00769 0.00234 -0.1201 0.6024 0.4931
1.500 0.7098 0.00728 0.00241 -0.1202 0.5975 0.6567
1.750 0.7350 0.00697 0.00250 -0.1196 0.5919 0.7960
2.000 0.7576 0.00685 0.00261 -0.1182 0.5861 0.8889
2.250 0.7818 0.00681 0.00268 -0.1171 0.5806 0.9467
2.500 0.8142 0.00688 0.00273 -0.1179 0.5736 0.9788
2.750 0.8513 0.00698 0.00279 -0.1200 0.5663 0.9930
3.000 0.8911 0.00708 0.00285 -0.1227 0.5569 0.9992
3.250 0.9175 0.00719 0.00291 -0.1225 0.5466 1.0000
3.500 0.9412 0.00733 0.00297 -0.1217 0.5335 1.0000
3.750 0.9651 0.00750 0.00306 -0.1209 0.5179 1.0000
4.000 0.9890 0.00769 0.00317 -0.1202 0.5003 1.0000
4.250 1.0126 0.00792 0.00330 -0.1195 0.4801 1.0000
4.500 1.0354 0.00820 0.00347 -0.1186 0.4582 1.0000
5.000 1.0782 0.00891 0.00392 -0.1163 0.4102 1.0000
5.250 1.1000 0.00924 0.00415 -0.1153 0.3920 1.0000
5.500 1.1223 0.00954 0.00437 -0.1144 0.3785 1.0000
6.000 1.1674 0.01008 0.00481 -0.1126 0.3579 1.0000
6.250 1.1888 0.01038 0.00505 -0.1115 0.3496 1.0000
6.500 1.2118 0.01059 0.00526 -0.1107 0.3434 1.0000
6.750 1.2327 0.01086 0.00550 -0.1095 0.3367 1.0000
7.000 1.2513 0.01116 0.00577 -0.1079 0.3307 1.0000
7.250 1.2730 0.01137 0.00598 -0.1069 0.3266 1.0000
7.500 1.2936 0.01163 0.00625 -0.1056 0.3221 1.0000
7.750 1.3127 0.01197 0.00656 -0.1042 0.3172 1.0000
8.000 1.3331 0.01227 0.00687 -0.1030 0.3130 1.0000
8.250 1.3552 0.01251 0.00713 -0.1022 0.3093 1.0000
8.500 1.3758 0.01282 0.00745 -0.1011 0.3051 1.0000
8.750 1.3945 0.01322 0.00783 -0.0998 0.3001 1.0000
9.000 1.4146 0.01356 0.00819 -0.0987 0.2957 1.0000
9.250 1.4362 0.01385 0.00850 -0.0979 0.2911 1.0000
9.500 1.4549 0.01428 0.00892 -0.0967 0.2854 1.0000
9.750 1.4732 0.01473 0.00937 -0.0954 0.2793 1.0000
10.000 1.4932 0.01512 0.00976 -0.0944 0.2721 1.0000
10.250 1.5092 0.01571 0.01032 -0.0929 0.2638 1.0000
10.500 1.5273 0.01621 0.01081 -0.0917 0.2539 1.0000
10.750 1.5422 0.01688 0.01145 -0.0902 0.2418 1.0000
11.000 1.5545 0.01772 0.01222 -0.0883 0.2263 1.0000
11.250 1.5614 0.01890 0.01328 -0.0858 0.2047 1.0000
11.500 1.5658 0.02027 0.01452 -0.0831 0.1846 1.0000
11.750 1.5722 0.02157 0.01576 -0.0808 0.1715 1.0000
12.250 1.5915 0.02388 0.01803 -0.0773 0.1559 1.0000
12.500 1.6012 0.02508 0.01923 -0.0756 0.1503 1.0000
12.750 1.6121 0.02623 0.02040 -0.0742 0.1454 1.0000
13.000 1.6241 0.02733 0.02151 -0.0730 0.1408 1.0000
13.250 1.6323 0.02874 0.02292 -0.0715 0.1354 1.0000
13.500 1.6434 0.02996 0.02417 -0.0703 0.1311 1.0000
13.750 1.6541 0.03124 0.02546 -0.0692 0.1267 1.0000
14.000 1.6617 0.03280 0.02703 -0.0678 0.1220 1.0000
14.250 1.6723 0.03415 0.02842 -0.0668 0.1182 1.0000
14.500 1.6808 0.03570 0.02997 -0.0657 0.1132 1.0000
14.750 1.6868 0.03748 0.03175 -0.0645 0.1083 1.0000
15.000 1.6954 0.03905 0.03336 -0.0636 0.1039 1.0000
15.250 1.6998 0.04103 0.03532 -0.0624 0.0987 1.0000
15.500 1.7066 0.04284 0.03717 -0.0615 0.0945 1.0000
15.750 1.7103 0.04494 0.03927 -0.0605 0.0895 1.0000
16.000 1.7144 0.04702 0.04138 -0.0595 0.0852 1.0000
16.250 1.7161 0.04938 0.04375 -0.0585 0.0803 1.0000
16.500 1.7184 0.05172 0.04611 -0.0576 0.0758 1.0000
16.750 1.7175 0.05444 0.04883 -0.0567 0.0709 1.0000
17.000 1.7173 0.05712 0.05154 -0.0560 0.0665 1.0000
17.250 1.7136 0.06019 0.05462 -0.0552 0.0617 1.0000
17.500 1.7110 0.06322 0.05768 -0.0545 0.0568 1.0000
17.750 1.7052 0.06669 0.06116 -0.0539 0.0517 1.0000
18.000 1.6970 0.07048 0.06497 -0.0534 0.0464 1.0000
18.250 1.6860 0.07465 0.06915 -0.0530 0.0401 1.0000
18.500 1.6727 0.07921 0.07372 -0.0528 0.0339 1.0000
18.750 1.6577 0.08410 0.07863 -0.0527 0.0284 1.0000
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