GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.25 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe289-il-1000000-n5.txt Download as CSV file: xf-goe289-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 289 (MVA 289) 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5520 0.07015 0.06763 -0.1027 0.9760 0.0209
-14.750 -0.5870 0.05968 0.05697 -0.1119 0.9660 0.0210
-14.500 -0.6008 0.05058 0.04768 -0.1230 0.9543 0.0211
-14.250 -0.5960 0.04216 0.03902 -0.1368 0.9396 0.0211
-14.000 -0.5669 0.03488 0.03146 -0.1531 0.9262 0.0212
-13.750 -0.5353 0.02951 0.02582 -0.1664 0.9099 0.0213
-13.500 -0.5252 0.02627 0.02234 -0.1720 0.8918 0.0213
-13.250 -0.5242 0.02456 0.02045 -0.1721 0.8748 0.0214
-13.000 -0.5248 0.02344 0.01918 -0.1699 0.8586 0.0214
-12.750 -0.5261 0.02255 0.01815 -0.1665 0.8425 0.0215
-12.500 -0.5264 0.02183 0.01730 -0.1629 0.8259 0.0215
-12.250 -0.5173 0.02123 0.01658 -0.1605 0.8093 0.0216
-12.000 -0.5078 0.02061 0.01581 -0.1581 0.7909 0.0216
-11.750 -0.4972 0.01997 0.01502 -0.1559 0.7737 0.0217
-11.500 -0.4848 0.01931 0.01423 -0.1539 0.7597 0.0217
-11.250 -0.4733 0.01847 0.01327 -0.1518 0.7483 0.0219
-11.000 -0.4588 0.01781 0.01251 -0.1500 0.7383 0.0221
-10.750 -0.4414 0.01725 0.01186 -0.1486 0.7294 0.0222
-10.500 -0.4231 0.01677 0.01129 -0.1472 0.7210 0.0223
-10.250 -0.4029 0.01630 0.01076 -0.1462 0.7145 0.0224
-10.000 -0.3823 0.01590 0.01028 -0.1451 0.7076 0.0226
-9.750 -0.3613 0.01549 0.00981 -0.1440 0.7012 0.0227
-9.500 -0.3385 0.01518 0.00945 -0.1433 0.6949 0.0230
-9.250 -0.3169 0.01481 0.00901 -0.1423 0.6884 0.0231
-9.000 -0.2940 0.01448 0.00862 -0.1415 0.6830 0.0233
-8.750 -0.2711 0.01413 0.00821 -0.1407 0.6768 0.0235
-8.500 -0.2484 0.01382 0.00782 -0.1398 0.6702 0.0237
-8.250 -0.2251 0.01349 0.00744 -0.1390 0.6646 0.0238
-8.000 -0.2013 0.01320 0.00709 -0.1383 0.6581 0.0240
-7.750 -0.1781 0.01293 0.00674 -0.1374 0.6514 0.0242
-7.500 -0.1538 0.01265 0.00641 -0.1368 0.6451 0.0244
-7.250 -0.1298 0.01240 0.00610 -0.1360 0.6376 0.0245
-7.000 -0.1058 0.01217 0.00581 -0.1353 0.6307 0.0247
-6.750 -0.0813 0.01195 0.00553 -0.1346 0.6225 0.0249
-6.500 -0.0573 0.01176 0.00527 -0.1339 0.6142 0.0250
-6.250 -0.0326 0.01157 0.00502 -0.1332 0.6055 0.0252
-6.000 -0.0083 0.01141 0.00479 -0.1325 0.5966 0.0253
-5.750 0.0163 0.01126 0.00458 -0.1318 0.5864 0.0255
-5.500 0.0399 0.01105 0.00430 -0.1309 0.5765 0.0258
-5.250 0.0636 0.01087 0.00404 -0.1301 0.5664 0.0261
-5.000 0.0882 0.01070 0.00383 -0.1294 0.5583 0.0265
-4.750 0.1129 0.01058 0.00366 -0.1287 0.5503 0.0269
-4.500 0.1379 0.01046 0.00350 -0.1281 0.5435 0.0272
-4.250 0.1631 0.01037 0.00336 -0.1275 0.5360 0.0276
-4.000 0.1879 0.01029 0.00324 -0.1268 0.5290 0.0281
-3.750 0.2135 0.01020 0.00311 -0.1263 0.5228 0.0286
-3.500 0.2387 0.01013 0.00301 -0.1257 0.5167 0.0291
-3.250 0.2639 0.01008 0.00291 -0.1251 0.5109 0.0295
-3.000 0.2894 0.01001 0.00281 -0.1246 0.5049 0.0299
-2.750 0.3142 0.00994 0.00270 -0.1239 0.4988 0.0310
-2.500 0.3393 0.00988 0.00262 -0.1233 0.4935 0.0319
-2.250 0.3649 0.00982 0.00255 -0.1227 0.4886 0.0331
-2.000 0.3900 0.00979 0.00249 -0.1221 0.4833 0.0346
-1.750 0.4145 0.00976 0.00244 -0.1214 0.4780 0.0382
-1.500 0.4382 0.00953 0.00235 -0.1206 0.4732 0.0742
-1.250 0.4625 0.00948 0.00233 -0.1199 0.4670 0.0905
-1.000 0.4865 0.00947 0.00233 -0.1191 0.4615 0.1029
-0.750 0.5118 0.00945 0.00232 -0.1185 0.4569 0.1121
-0.500 0.5365 0.00944 0.00233 -0.1179 0.4518 0.1212
-0.250 0.5603 0.00945 0.00234 -0.1171 0.4464 0.1306
0.000 0.5848 0.00946 0.00235 -0.1163 0.4420 0.1402
0.250 0.6091 0.00945 0.00237 -0.1156 0.4370 0.1509
0.500 0.6324 0.00949 0.00239 -0.1147 0.4310 0.1613
0.750 0.6547 0.00948 0.00242 -0.1136 0.4255 0.1822
1.000 0.6759 0.00939 0.00245 -0.1123 0.4203 0.2289
1.250 0.6959 0.00934 0.00251 -0.1107 0.4146 0.2796
1.500 0.7169 0.00934 0.00259 -0.1094 0.4099 0.3128
1.750 0.7394 0.00937 0.00265 -0.1083 0.4052 0.3345
2.000 0.7611 0.00943 0.00273 -0.1071 0.4000 0.3535
2.250 0.7820 0.00953 0.00283 -0.1057 0.3948 0.3681
2.500 0.8044 0.00960 0.00292 -0.1046 0.3906 0.3810
2.750 0.8262 0.00969 0.00302 -0.1035 0.3854 0.3923
3.250 0.8684 0.00991 0.00326 -0.1009 0.3753 0.4212
3.500 0.8891 0.00998 0.00339 -0.0996 0.3702 0.4462
3.750 0.9083 0.01004 0.00355 -0.0980 0.3657 0.4924
4.000 0.9242 0.00995 0.00376 -0.0958 0.3616 0.6198
4.250 0.9367 0.00973 0.00395 -0.0927 0.3586 0.7690
5.000 1.1061 0.01017 0.00470 -0.1124 0.3439 1.0000
5.250 1.1273 0.01033 0.00485 -0.1112 0.3410 1.0000
5.500 1.1482 0.01051 0.00502 -0.1101 0.3376 1.0000
5.750 1.1683 0.01072 0.00522 -0.1088 0.3340 1.0000
6.000 1.1878 0.01096 0.00543 -0.1074 0.3303 1.0000
6.250 1.2092 0.01115 0.00563 -0.1064 0.3278 1.0000
6.500 1.2305 0.01135 0.00583 -0.1054 0.3252 1.0000
6.750 1.2513 0.01157 0.00605 -0.1043 0.3225 1.0000
7.000 1.2717 0.01181 0.00630 -0.1032 0.3199 1.0000
7.250 1.2915 0.01209 0.00657 -0.1021 0.3172 1.0000
7.500 1.3107 0.01240 0.00687 -0.1008 0.3144 1.0000
7.750 1.3316 0.01265 0.00713 -0.0999 0.3121 1.0000
8.000 1.3518 0.01293 0.00742 -0.0989 0.3083 1.0000
8.250 1.3703 0.01329 0.00777 -0.0977 0.3034 1.0000
8.500 1.3870 0.01374 0.00820 -0.0962 0.2983 1.0000
8.750 1.4071 0.01406 0.00853 -0.0953 0.2945 1.0000
9.000 1.4257 0.01444 0.00892 -0.0942 0.2896 1.0000
9.250 1.4420 0.01495 0.00941 -0.0929 0.2845 1.0000
9.500 1.4599 0.01540 0.00986 -0.0917 0.2800 1.0000
9.750 1.4783 0.01583 0.01031 -0.0907 0.2764 1.0000
10.000 1.4951 0.01634 0.01083 -0.0896 0.2721 1.0000
10.250 1.5096 0.01699 0.01147 -0.0881 0.2670 1.0000
10.500 1.5272 0.01749 0.01200 -0.0871 0.2628 1.0000
10.750 1.5397 0.01829 0.01277 -0.0856 0.2543 1.0000
11.000 1.5541 0.01900 0.01348 -0.0843 0.2482 1.0000
11.250 1.5627 0.02005 0.01449 -0.0825 0.2371 1.0000
11.500 1.5722 0.02111 0.01552 -0.0808 0.2262 1.0000
11.750 1.5741 0.02268 0.01701 -0.0785 0.2099 1.0000
12.000 1.5638 0.02514 0.01933 -0.0752 0.1831 1.0000
12.250 1.5294 0.02961 0.02355 -0.0705 0.1386 1.0000
12.500 1.5030 0.03387 0.02766 -0.0671 0.1048 1.0000
12.750 1.4841 0.03778 0.03149 -0.0647 0.0824 1.0000
13.000 1.4786 0.04067 0.03437 -0.0633 0.0716 1.0000
13.250 1.4677 0.04417 0.03785 -0.0618 0.0570 1.0000
13.500 1.4436 0.04916 0.04276 -0.0602 0.0344 1.0000
13.750 1.4384 0.05239 0.04602 -0.0594 0.0288 1.0000
14.000 1.4347 0.05554 0.04922 -0.0588 0.0251 1.0000
14.250 1.4329 0.05854 0.05227 -0.0583 0.0232 1.0000
14.500 1.4312 0.06158 0.05536 -0.0580 0.0214 1.0000
14.750 1.4297 0.06464 0.05848 -0.0577 0.0202 1.0000
15.000 1.4279 0.06776 0.06166 -0.0574 0.0191 1.0000
15.250 1.4257 0.07097 0.06493 -0.0572 0.0184 1.0000
15.500 1.4229 0.07429 0.06832 -0.0571 0.0177 1.0000
15.750 1.4192 0.07776 0.07184 -0.0571 0.0168 1.0000
16.000 1.4154 0.08128 0.07542 -0.0571 0.0163 1.0000
16.250 1.4122 0.08474 0.07895 -0.0572 0.0158 1.0000
16.500 1.4092 0.08818 0.08247 -0.0573 0.0153 1.0000
16.750 1.4050 0.09184 0.08619 -0.0575 0.0149 1.0000
17.000 1.4005 0.09559 0.09001 -0.0578 0.0145 1.0000
17.250 1.3969 0.09919 0.09366 -0.0581 0.0141 1.0000
17.500 1.3918 0.10304 0.09758 -0.0586 0.0139 1.0000
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Polar data table (+)
Polar graphs
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