GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 200,000 Max Cl/Cd: 80.19 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe369-il-200000.txt Download as CSV file: xf-goe369-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 369 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3434 0.09339 0.08999 -0.0113 1.0000 0.0190
-7.500 -0.3398 0.09080 0.08744 -0.0119 1.0000 0.0195
-7.250 -0.3371 0.08834 0.08503 -0.0126 1.0000 0.0202
-7.000 -0.3304 0.08568 0.08242 -0.0145 1.0000 0.0210
-6.750 -0.3192 0.08344 0.08021 -0.0187 1.0000 0.0218
-6.500 -0.3035 0.08132 0.07810 -0.0246 1.0000 0.0221
-6.250 -0.2860 0.07875 0.07551 -0.0290 1.0000 0.0222
-6.000 -0.2683 0.07594 0.07268 -0.0323 1.0000 0.0223
-5.500 -0.2516 0.06782 0.06465 -0.0321 1.0000 0.0227
-5.250 -0.2461 0.06453 0.06144 -0.0307 1.0000 0.0231
-5.000 -0.2411 0.06207 0.05905 -0.0298 1.0000 0.0235
-4.750 -0.2027 0.05767 0.05459 -0.0364 0.9905 0.0245
-4.500 -0.1575 0.05331 0.05013 -0.0442 0.9770 0.0258
-4.250 -0.1102 0.04920 0.04587 -0.0517 0.9614 0.0275
-4.000 -0.0464 0.04663 0.04291 -0.0602 0.9440 0.0295
-3.750 -0.0047 0.04206 0.03810 -0.0653 0.9238 0.0301
-3.500 0.0225 0.03766 0.03369 -0.0683 0.9014 0.0317
-3.250 0.0538 0.03501 0.03084 -0.0702 0.8788 0.0338
-3.000 0.0952 0.03503 0.03026 -0.0708 0.8585 0.0393
-2.750 0.1140 0.03053 0.02568 -0.0714 0.8420 0.0413
-2.500 0.1371 0.02860 0.02360 -0.0713 0.8271 0.0441
-2.250 0.1713 0.02928 0.02368 -0.0703 0.8136 0.0511
-2.000 0.1910 0.02525 0.01965 -0.0707 0.8014 0.0541
-1.750 0.2218 0.02653 0.02038 -0.0694 0.7882 0.0640
-1.500 0.2416 0.02248 0.01643 -0.0696 0.7760 0.0693
-1.250 0.2676 0.02130 0.01498 -0.0690 0.7647 0.0815
-1.000 0.2930 0.02014 0.01365 -0.0686 0.7544 0.0988
-0.750 0.3173 0.01900 0.01236 -0.0684 0.7451 0.1353
0.000 0.4085 0.01584 0.00810 -0.0647 0.7210 0.0621
0.250 0.4358 0.01490 0.00703 -0.0640 0.7121 0.0612
0.500 0.4628 0.01405 0.00605 -0.0632 0.7040 0.0582
0.750 0.4892 0.01343 0.00536 -0.0624 0.6948 0.0581
1.000 0.5151 0.01311 0.00501 -0.0616 0.6844 0.0632
1.250 0.5403 0.01263 0.00452 -0.0608 0.6747 0.0661
1.500 0.5661 0.01242 0.00429 -0.0600 0.6648 0.0748
1.750 0.5919 0.01224 0.00408 -0.0593 0.6538 0.0875
2.000 0.6358 0.01024 0.00388 -0.0627 0.6426 1.0000
2.250 0.6615 0.01036 0.00382 -0.0619 0.6318 1.0000
2.500 0.6870 0.01045 0.00379 -0.0612 0.6196 1.0000
2.750 0.7124 0.01054 0.00381 -0.0605 0.6064 1.0000
3.000 0.7378 0.01062 0.00383 -0.0597 0.5928 1.0000
3.250 0.7630 0.01070 0.00386 -0.0590 0.5777 1.0000
3.500 0.7881 0.01077 0.00386 -0.0582 0.5614 1.0000
3.750 0.8132 0.01086 0.00391 -0.0574 0.5443 1.0000
4.000 0.8382 0.01095 0.00398 -0.0567 0.5249 1.0000
4.250 0.8631 0.01107 0.00408 -0.0559 0.5048 1.0000
4.500 0.8878 0.01122 0.00419 -0.0552 0.4820 1.0000
4.750 0.9121 0.01141 0.00432 -0.0544 0.4558 1.0000
5.000 0.9358 0.01167 0.00448 -0.0536 0.4246 1.0000
5.250 0.9586 0.01206 0.00470 -0.0526 0.3886 1.0000
5.500 0.9805 0.01256 0.00506 -0.0516 0.3488 1.0000
5.750 1.0018 0.01318 0.00549 -0.0506 0.3077 1.0000
6.000 1.0228 0.01387 0.00598 -0.0496 0.2669 1.0000
6.250 1.0436 0.01460 0.00652 -0.0486 0.2322 1.0000
6.500 1.0645 0.01535 0.00715 -0.0476 0.2065 1.0000
6.750 1.0845 0.01620 0.00784 -0.0466 0.1882 1.0000
7.000 1.1046 0.01706 0.00861 -0.0455 0.1737 1.0000
7.250 1.1259 0.01778 0.00934 -0.0446 0.1619 1.0000
7.500 1.1472 0.01853 0.01013 -0.0437 0.1523 1.0000
7.750 1.1675 0.01945 0.01101 -0.0427 0.1443 1.0000
8.000 1.1894 0.02003 0.01170 -0.0419 0.1364 1.0000
8.250 1.2098 0.02096 0.01261 -0.0410 0.1301 1.0000
8.500 1.2314 0.02160 0.01340 -0.0401 0.1239 1.0000
8.750 1.2514 0.02267 0.01442 -0.0392 0.1183 1.0000
9.000 1.2724 0.02339 0.01536 -0.0382 0.1131 1.0000
9.250 1.2926 0.02421 0.01624 -0.0373 0.1081 1.0000
9.500 1.3127 0.02552 0.01759 -0.0364 0.1035 1.0000
9.750 1.3314 0.02620 0.01851 -0.0353 0.0981 1.0000
10.000 1.3495 0.02738 0.01959 -0.0344 0.0920 1.0000
10.250 1.3650 0.02771 0.02023 -0.0329 0.0864 1.0000
10.500 1.3804 0.02846 0.02101 -0.0317 0.0812 1.0000
10.750 1.3947 0.02944 0.02219 -0.0303 0.0763 1.0000
11.000 1.4076 0.03002 0.02295 -0.0287 0.0713 1.0000
11.250 1.4178 0.03114 0.02412 -0.0270 0.0665 1.0000
11.500 1.4248 0.03150 0.02476 -0.0245 0.0608 1.0000
11.750 1.4280 0.03241 0.02575 -0.0222 0.0547 1.0000
12.000 1.4298 0.03361 0.02703 -0.0203 0.0459 1.0000
12.250 1.4283 0.03571 0.02923 -0.0187 0.0373 1.0000
12.500 1.4239 0.03847 0.03214 -0.0174 0.0323 1.0000
12.750 1.4184 0.04148 0.03521 -0.0169 0.0289 1.0000
13.000 1.4111 0.04496 0.03882 -0.0165 0.0267 1.0000
13.250 1.4088 0.04806 0.04212 -0.0165 0.0248 1.0000
13.500 1.4043 0.05151 0.04573 -0.0170 0.0232 1.0000
13.750 1.3973 0.05540 0.04975 -0.0176 0.0223 1.0000
14.000 1.3872 0.05982 0.05427 -0.0186 0.0215 1.0000
14.250 1.3748 0.06469 0.05925 -0.0196 0.0208 1.0000
14.500 1.3647 0.06947 0.06419 -0.0208 0.0204 1.0000
14.750 1.3553 0.07437 0.06930 -0.0224 0.0200 1.0000
15.000 1.3446 0.07965 0.07477 -0.0244 0.0198 1.0000
15.250 1.3329 0.08537 0.08069 -0.0268 0.0195 1.0000
15.500 1.3197 0.09167 0.08718 -0.0297 0.0193 1.0000
15.750 1.3060 0.09834 0.09404 -0.0331 0.0192 1.0000
16.000 1.2910 0.10560 0.10148 -0.0369 0.0192 1.0000
16.250 1.2746 0.11346 0.10953 -0.0413 0.0191 1.0000
16.500 1.2570 0.12188 0.11812 -0.0461 0.0193 1.0000
16.750 1.2379 0.13106 0.12747 -0.0516 0.0194 1.0000
17.000 1.2176 0.14090 0.13746 -0.0576 0.0197 1.0000
17.250 1.1953 0.15176 0.14843 -0.0643 0.0200 1.0000
17.500 1.1711 0.16368 0.16045 -0.0716 0.0205 1.0000
17.750 1.0531 0.21873 0.21524 -0.0996 0.0323 1.0000
18.000 1.0561 0.22450 0.22099 -0.1024 0.0338 1.0000
18.250 1.0618 0.22927 0.22577 -0.1044 0.0348 1.0000
18.500 1.0740 0.22758 0.22414 -0.1042 0.0274 1.0000
18.750 0.8548 0.22521 0.22233 -0.0923 0.0455 1.0000
19.000 0.8568 0.22996 0.22710 -0.0942 0.0455 1.0000
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