GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.93 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe289-il-1000000.txt Download as CSV file: xf-goe289-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.1664 0.12764 0.12587 -0.0745 0.9862 0.0255
-13.500 -0.1498 0.12499 0.12322 -0.0771 0.9835 0.0257
-13.250 -0.4650 0.05452 0.05213 -0.1199 0.9724 0.0253
-12.500 -0.4550 0.03071 0.02741 -0.1636 0.9365 0.0253
-12.250 -0.4485 0.02693 0.02328 -0.1672 0.9179 0.0254
-12.000 -0.4424 0.02539 0.02154 -0.1661 0.9023 0.0255
-11.750 -0.4357 0.02400 0.01999 -0.1644 0.8886 0.0257
-11.500 -0.4258 0.02299 0.01887 -0.1625 0.8756 0.0259
-11.250 -0.4154 0.02210 0.01787 -0.1604 0.8632 0.0260
-11.000 -0.4029 0.02129 0.01693 -0.1586 0.8506 0.0262
-10.750 -0.3886 0.02061 0.01613 -0.1568 0.8375 0.0263
-10.500 -0.3737 0.01993 0.01533 -0.1550 0.8231 0.0265
-10.250 -0.3566 0.01940 0.01471 -0.1535 0.8088 0.0268
-10.000 -0.3398 0.01879 0.01397 -0.1520 0.7945 0.0271
-9.750 -0.3226 0.01815 0.01320 -0.1504 0.7811 0.0272
-9.500 -0.3046 0.01757 0.01248 -0.1489 0.7689 0.0274
-9.250 -0.2854 0.01697 0.01177 -0.1476 0.7581 0.0275
-9.000 -0.2655 0.01642 0.01111 -0.1464 0.7489 0.0277
-8.750 -0.2448 0.01593 0.01051 -0.1452 0.7398 0.0279
-8.500 -0.2236 0.01545 0.00993 -0.1442 0.7320 0.0282
-8.250 -0.2017 0.01498 0.00938 -0.1432 0.7244 0.0283
-8.000 -0.1798 0.01458 0.00888 -0.1421 0.7172 0.0285
-7.750 -0.1567 0.01415 0.00839 -0.1413 0.7107 0.0287
-7.500 -0.1336 0.01384 0.00799 -0.1404 0.7036 0.0289
-7.250 -0.1100 0.01354 0.00762 -0.1397 0.6974 0.0291
-7.000 -0.0862 0.01319 0.00722 -0.1389 0.6908 0.0293
-6.750 -0.0668 0.01247 0.00642 -0.1375 0.6838 0.0298
-6.500 -0.0440 0.01202 0.00595 -0.1366 0.6776 0.0302
-6.250 -0.0204 0.01172 0.00561 -0.1358 0.6704 0.0306
-6.000 0.0031 0.01147 0.00530 -0.1349 0.6633 0.0310
-5.750 0.0277 0.01120 0.00499 -0.1342 0.6560 0.0314
-5.500 0.0514 0.01100 0.00472 -0.1334 0.6481 0.0318
-5.250 0.0763 0.01077 0.00445 -0.1327 0.6407 0.0322
-5.000 0.1006 0.01059 0.00421 -0.1319 0.6327 0.0326
-4.750 0.1254 0.01042 0.00399 -0.1313 0.6250 0.0330
-4.500 0.1501 0.01027 0.00379 -0.1306 0.6164 0.0334
-4.250 0.1748 0.01012 0.00358 -0.1298 0.6084 0.0338
-4.000 0.1987 0.00989 0.00330 -0.1290 0.5998 0.0348
-3.750 0.2232 0.00975 0.00311 -0.1282 0.5919 0.0357
-3.500 0.2481 0.00964 0.00295 -0.1276 0.5837 0.0368
-3.250 0.2728 0.00956 0.00283 -0.1268 0.5759 0.0381
-3.000 0.2978 0.00946 0.00269 -0.1262 0.5679 0.0398
-2.750 0.3218 0.00938 0.00257 -0.1253 0.5601 0.0429
-2.500 0.3462 0.00918 0.00244 -0.1246 0.5530 0.0590
-2.250 0.3691 0.00901 0.00238 -0.1236 0.5459 0.0982
-2.000 0.3944 0.00895 0.00236 -0.1231 0.5399 0.1125
-1.750 0.4197 0.00894 0.00234 -0.1225 0.5334 0.1224
-1.500 0.4437 0.00894 0.00233 -0.1217 0.5266 0.1317
-1.250 0.4695 0.00892 0.00231 -0.1212 0.5209 0.1401
-1.000 0.4940 0.00891 0.00230 -0.1205 0.5145 0.1504
-0.750 0.5180 0.00890 0.00230 -0.1197 0.5087 0.1629
-0.500 0.5431 0.00884 0.00228 -0.1191 0.5036 0.1811
-0.250 0.5664 0.00875 0.00229 -0.1182 0.4980 0.2172
0.000 0.5882 0.00866 0.00233 -0.1171 0.4924 0.2765
0.250 0.6127 0.00859 0.00237 -0.1164 0.4876 0.3189
0.500 0.6366 0.00861 0.00242 -0.1156 0.4818 0.3468
0.750 0.6591 0.00868 0.00249 -0.1145 0.4758 0.3665
1.000 0.6840 0.00867 0.00253 -0.1139 0.4710 0.3867
1.250 0.7070 0.00870 0.00257 -0.1129 0.4655 0.4022
1.500 0.7275 0.00876 0.00262 -0.1114 0.4599 0.4158
1.750 0.7504 0.00877 0.00266 -0.1103 0.4554 0.4309
2.000 0.7722 0.00878 0.00272 -0.1091 0.4500 0.4516
2.250 0.7917 0.00879 0.00280 -0.1075 0.4445 0.4886
2.500 0.8099 0.00866 0.00293 -0.1056 0.4397 0.5899
2.750 0.8239 0.00843 0.00308 -0.1027 0.4347 0.7305
3.000 0.9685 0.00852 0.00359 -0.1286 0.4232 1.0000
3.250 0.9894 0.00864 0.00367 -0.1272 0.4178 1.0000
3.500 1.0071 0.00878 0.00377 -0.1252 0.4124 1.0000
3.750 1.0246 0.00892 0.00388 -0.1231 0.4074 1.0000
4.000 1.0441 0.00903 0.00397 -0.1214 0.4025 1.0000
4.250 1.0623 0.00919 0.00409 -0.1195 0.3971 1.0000
4.500 1.0802 0.00937 0.00423 -0.1176 0.3919 1.0000
4.750 1.1013 0.00950 0.00435 -0.1163 0.3876 1.0000
5.000 1.1210 0.00967 0.00450 -0.1148 0.3827 1.0000
5.250 1.1392 0.00990 0.00468 -0.1131 0.3774 1.0000
5.500 1.1605 0.01005 0.00484 -0.1120 0.3735 1.0000
5.750 1.1813 0.01023 0.00500 -0.1107 0.3692 1.0000
6.000 1.2007 0.01046 0.00520 -0.1093 0.3646 1.0000
6.250 1.2191 0.01073 0.00545 -0.1077 0.3600 1.0000
6.500 1.2412 0.01090 0.00563 -0.1069 0.3571 1.0000
6.750 1.2622 0.01110 0.00584 -0.1058 0.3537 1.0000
7.000 1.2819 0.01136 0.00609 -0.1045 0.3500 1.0000
7.250 1.3000 0.01168 0.00638 -0.1031 0.3463 1.0000
7.500 1.3201 0.01195 0.00665 -0.1019 0.3432 1.0000
7.750 1.3418 0.01216 0.00689 -0.1011 0.3402 1.0000
8.000 1.3613 0.01245 0.00718 -0.1000 0.3357 1.0000
8.250 1.3785 0.01285 0.00755 -0.0985 0.3308 1.0000
8.500 1.3974 0.01319 0.00789 -0.0973 0.3272 1.0000
8.750 1.4186 0.01344 0.00817 -0.0965 0.3222 1.0000
9.000 1.4369 0.01383 0.00855 -0.0954 0.3184 1.0000
9.250 1.4527 0.01433 0.00903 -0.0938 0.3140 1.0000
9.500 1.4724 0.01467 0.00941 -0.0929 0.3111 1.0000
9.750 1.4924 0.01501 0.00978 -0.0921 0.3079 1.0000
10.000 1.5107 0.01544 0.01022 -0.0911 0.3042 1.0000
10.250 1.5255 0.01604 0.01080 -0.0896 0.2995 1.0000
10.500 1.5429 0.01652 0.01132 -0.0885 0.2960 1.0000
10.750 1.5620 0.01694 0.01176 -0.0877 0.2917 1.0000
11.000 1.5776 0.01755 0.01237 -0.0865 0.2869 1.0000
11.250 1.5905 0.01831 0.01313 -0.0850 0.2818 1.0000
11.500 1.6089 0.01879 0.01366 -0.0842 0.2776 1.0000
11.750 1.6216 0.01960 0.01446 -0.0828 0.2702 1.0000
12.000 1.6344 0.02043 0.01529 -0.0815 0.2625 1.0000
12.250 1.6419 0.02162 0.01644 -0.0797 0.2520 1.0000
12.500 1.6462 0.02305 0.01781 -0.0777 0.2355 1.0000
12.750 1.6384 0.02537 0.01999 -0.0747 0.2102 1.0000
13.000 1.6218 0.02850 0.02296 -0.0714 0.1809 1.0000
13.250 1.5857 0.03341 0.02764 -0.0672 0.1410 1.0000
13.500 1.5571 0.03810 0.03220 -0.0642 0.1104 1.0000
13.750 1.5292 0.04304 0.03706 -0.0618 0.0863 1.0000
14.000 1.5096 0.04745 0.04143 -0.0602 0.0695 1.0000
14.250 1.4869 0.05242 0.04635 -0.0588 0.0499 1.0000
14.500 1.4648 0.05753 0.05143 -0.0578 0.0347 1.0000
14.750 1.4519 0.06183 0.05576 -0.0572 0.0290 1.0000
15.000 1.4464 0.06536 0.05936 -0.0569 0.0267 1.0000
15.250 1.4369 0.06939 0.06344 -0.0566 0.0244 1.0000
15.500 1.4340 0.07271 0.06683 -0.0564 0.0235 1.0000
15.750 1.4283 0.07643 0.07062 -0.0564 0.0225 1.0000
16.000 1.4212 0.08036 0.07462 -0.0564 0.0216 1.0000
16.250 1.4148 0.08422 0.07855 -0.0565 0.0211 1.0000
16.500 1.4092 0.08801 0.08241 -0.0566 0.0204 1.0000
16.750 1.4040 0.09182 0.08630 -0.0568 0.0199 1.0000
17.000 1.3995 0.09557 0.09013 -0.0571 0.0195 1.0000
17.250 1.3948 0.09934 0.09396 -0.0575 0.0191 1.0000
17.500 1.3878 0.10345 0.09815 -0.0580 0.0186 1.0000
17.750 1.3810 0.10760 0.10236 -0.0585 0.0182 1.0000
18.000 1.3731 0.11192 0.10674 -0.0592 0.0178 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 289 (MVA 289) AIRFOIL (goe289-il)