GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 412 AIRFOIL (goe412-il) Reynolds number: 200,000 Max Cl/Cd: 79.53 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe412-il-200000-n5.txt Download as CSV file: xf-goe412-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 412 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2088 0.08660 0.08276 -0.0848 0.9605 0.0351
-9.500 -0.2073 0.08176 0.07792 -0.0882 0.9511 0.0352
-9.250 -0.2071 0.07674 0.07289 -0.0917 0.9415 0.0350
-9.000 -0.2118 0.07121 0.06736 -0.0955 0.9295 0.0349
-8.750 -0.2262 0.06476 0.06093 -0.1003 0.9124 0.0348
-8.500 -0.3083 0.03535 0.03037 -0.1223 0.8861 0.0347
-8.250 -0.3014 0.03117 0.02559 -0.1225 0.8760 0.0352
-8.000 -0.2852 0.02833 0.02224 -0.1224 0.8693 0.0356
-7.750 -0.2664 0.02631 0.01981 -0.1220 0.8613 0.0359
-7.500 -0.2438 0.02465 0.01777 -0.1218 0.8555 0.0362
-7.250 -0.2211 0.02337 0.01619 -0.1214 0.8481 0.0365
-7.000 -0.1966 0.02219 0.01473 -0.1211 0.8421 0.0368
-6.750 -0.1723 0.02101 0.01342 -0.1209 0.8363 0.0374
-6.500 -0.1472 0.02021 0.01252 -0.1207 0.8298 0.0382
-6.250 -0.1209 0.01948 0.01165 -0.1206 0.8245 0.0389
-6.000 -0.0953 0.01880 0.01085 -0.1204 0.8185 0.0395
-5.750 -0.0692 0.01814 0.01007 -0.1201 0.8126 0.0400
-5.500 -0.0423 0.01754 0.00932 -0.1200 0.8077 0.0406
-5.250 -0.0163 0.01702 0.00871 -0.1198 0.8019 0.0413
-5.000 0.0101 0.01654 0.00814 -0.1195 0.7963 0.0419
-4.750 0.0373 0.01611 0.00759 -0.1194 0.7915 0.0426
-4.500 0.0639 0.01575 0.00715 -0.1192 0.7861 0.0434
-4.250 0.0902 0.01536 0.00673 -0.1190 0.7806 0.0445
-4.000 0.1175 0.01505 0.00638 -0.1190 0.7758 0.0463
-3.750 0.1448 0.01480 0.00607 -0.1189 0.7710 0.0486
-3.500 0.1716 0.01457 0.00580 -0.1187 0.7655 0.0509
-3.250 0.1989 0.01432 0.00556 -0.1186 0.7605 0.0544
-3.000 0.2270 0.01411 0.00531 -0.1186 0.7564 0.0606
-2.750 0.2536 0.01393 0.00517 -0.1184 0.7507 0.0723
-2.500 0.2808 0.01377 0.00502 -0.1183 0.7456 0.0863
-2.250 0.3087 0.01363 0.00488 -0.1183 0.7412 0.1006
-2.000 0.3360 0.01353 0.00483 -0.1183 0.7362 0.1167
-1.750 0.3631 0.01345 0.00477 -0.1182 0.7309 0.1331
-1.500 0.3908 0.01336 0.00466 -0.1182 0.7262 0.1470
-1.250 0.4184 0.01325 0.00456 -0.1182 0.7217 0.1629
-1.000 0.4450 0.01314 0.00453 -0.1180 0.7160 0.1811
-0.750 0.4718 0.01296 0.00451 -0.1179 0.7110 0.2232
-0.250 0.5251 0.01265 0.00453 -0.1177 0.7008 0.3429
0.000 0.5511 0.01244 0.00453 -0.1174 0.6952 0.4054
0.250 0.5762 0.01208 0.00452 -0.1169 0.6901 0.5359
0.500 0.5951 0.01137 0.00466 -0.1146 0.6820 0.8028
0.750 0.6596 0.01119 0.00456 -0.1219 0.6724 1.0000
1.000 0.6838 0.01126 0.00455 -0.1212 0.6629 1.0000
1.250 0.7089 0.01134 0.00453 -0.1206 0.6550 1.0000
1.500 0.7338 0.01143 0.00456 -0.1200 0.6471 1.0000
1.750 0.7594 0.01153 0.00457 -0.1195 0.6410 1.0000
2.000 0.7843 0.01165 0.00466 -0.1190 0.6336 1.0000
2.250 0.8099 0.01176 0.00469 -0.1185 0.6271 1.0000
2.500 0.8348 0.01188 0.00480 -0.1180 0.6198 1.0000
2.750 0.8600 0.01200 0.00486 -0.1174 0.6123 1.0000
3.000 0.8846 0.01213 0.00497 -0.1168 0.6037 1.0000
3.250 0.9095 0.01227 0.00504 -0.1162 0.5952 1.0000
3.500 0.9338 0.01241 0.00517 -0.1156 0.5861 1.0000
3.750 0.9584 0.01257 0.00528 -0.1150 0.5773 1.0000
4.000 0.9822 0.01273 0.00543 -0.1143 0.5672 1.0000
4.250 1.0062 0.01291 0.00558 -0.1136 0.5575 1.0000
4.500 1.0295 0.01310 0.00572 -0.1127 0.5463 1.0000
4.750 1.0521 0.01330 0.00591 -0.1118 0.5335 1.0000
5.000 1.0745 0.01353 0.00610 -0.1108 0.5207 1.0000
5.250 1.0959 0.01378 0.00631 -0.1097 0.5058 1.0000
5.500 1.1164 0.01406 0.00653 -0.1083 0.4892 1.0000
5.750 1.1365 0.01436 0.00679 -0.1070 0.4736 1.0000
6.000 1.1561 0.01469 0.00708 -0.1056 0.4581 1.0000
6.250 1.1752 0.01504 0.00739 -0.1041 0.4432 1.0000
6.500 1.1933 0.01542 0.00773 -0.1025 0.4278 1.0000
6.750 1.2100 0.01584 0.00810 -0.1006 0.4114 1.0000
7.000 1.2244 0.01630 0.00852 -0.0984 0.3948 1.0000
7.250 1.2375 0.01681 0.00897 -0.0959 0.3787 1.0000
7.500 1.2505 0.01736 0.00948 -0.0935 0.3631 1.0000
7.750 1.2636 0.01795 0.01003 -0.0912 0.3486 1.0000
8.000 1.2767 0.01858 0.01065 -0.0891 0.3352 1.0000
8.500 1.3019 0.01998 0.01200 -0.0848 0.3081 1.0000
8.750 1.3141 0.02074 0.01275 -0.0828 0.2940 1.0000
9.000 1.3259 0.02155 0.01355 -0.0807 0.2805 1.0000
9.250 1.3369 0.02244 0.01444 -0.0787 0.2666 1.0000
9.500 1.3467 0.02343 0.01541 -0.0766 0.2516 1.0000
9.750 1.3551 0.02454 0.01648 -0.0745 0.2358 1.0000
10.000 1.3625 0.02577 0.01766 -0.0724 0.2206 1.0000
10.250 1.3700 0.02705 0.01890 -0.0705 0.2074 1.0000
10.500 1.3778 0.02836 0.02021 -0.0686 0.1971 1.0000
10.750 1.3852 0.02974 0.02157 -0.0669 0.1882 1.0000
11.000 1.3944 0.03104 0.02290 -0.0654 0.1807 1.0000
11.250 1.4020 0.03247 0.02435 -0.0638 0.1738 1.0000
11.500 1.4109 0.03384 0.02578 -0.0624 0.1681 1.0000
11.750 1.4199 0.03523 0.02724 -0.0611 0.1614 1.0000
12.000 1.4251 0.03695 0.02897 -0.0597 0.1546 1.0000
12.250 1.4356 0.03827 0.03040 -0.0586 0.1461 1.0000
12.500 1.4425 0.03993 0.03210 -0.0574 0.1351 1.0000
12.750 1.4474 0.04182 0.03397 -0.0562 0.1108 1.0000
13.000 1.4391 0.04497 0.03687 -0.0545 0.0868 1.0000
13.250 1.4361 0.04772 0.03959 -0.0532 0.0772 1.0000
13.500 1.4346 0.05042 0.04231 -0.0520 0.0703 1.0000
13.750 1.4383 0.05265 0.04464 -0.0511 0.0622 1.0000
14.000 1.4384 0.05529 0.04731 -0.0502 0.0508 1.0000
14.250 1.4331 0.05861 0.05056 -0.0493 0.0371 1.0000
14.500 1.4272 0.06211 0.05404 -0.0487 0.0299 1.0000
14.750 1.4228 0.06555 0.05753 -0.0482 0.0263 1.0000
15.000 1.4187 0.06904 0.06111 -0.0478 0.0242 1.0000
15.250 1.4150 0.07257 0.06475 -0.0477 0.0227 1.0000
15.500 1.4102 0.07635 0.06864 -0.0477 0.0216 1.0000
15.750 1.4038 0.08042 0.07282 -0.0479 0.0208 1.0000
16.000 1.3991 0.08433 0.07685 -0.0482 0.0202 1.0000
16.250 1.3940 0.08838 0.08105 -0.0486 0.0196 1.0000
16.500 1.3880 0.09264 0.08544 -0.0493 0.0191 1.0000
16.750 1.3814 0.09707 0.09001 -0.0501 0.0186 1.0000
17.000 1.3740 0.10167 0.09474 -0.0510 0.0182 1.0000
17.250 1.3661 0.10643 0.09962 -0.0522 0.0178 1.0000
17.500 1.3573 0.11141 0.10471 -0.0536 0.0175 1.0000
17.750 1.3480 0.11655 0.10997 -0.0552 0.0172 1.0000
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