GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 460 AIRFOIL (goe460-il) Reynolds number: 50,000 Max Cl/Cd: 25.79 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe460-il-50000-n5.txt Download as CSV file: xf-goe460-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 460 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5747 0.11803 0.10857 -0.0455 1.0000 0.1701
-14.500 -0.6046 0.10659 0.09710 -0.0489 1.0000 0.1838
-14.000 -0.6503 0.09328 0.08375 -0.0527 1.0000 0.1995
-13.750 -0.6101 0.09723 0.08770 -0.0498 1.0000 0.2022
-13.500 -0.7723 0.07153 0.06183 -0.0583 1.0000 0.2165
-13.250 -0.6712 0.08252 0.07296 -0.0533 1.0000 0.2194
-13.000 -0.7353 0.07169 0.06204 -0.0556 1.0000 0.2286
-12.750 -0.8357 0.05934 0.04944 -0.0557 1.0000 0.2349
-12.500 -0.7854 0.06207 0.05231 -0.0545 1.0000 0.2413
-12.250 -0.8355 0.05599 0.04606 -0.0524 1.0000 0.2474
-12.000 -0.8756 0.05164 0.04155 -0.0490 1.0000 0.2524
-11.750 -0.8409 0.05229 0.04231 -0.0484 1.0000 0.2586
-11.500 -0.8574 0.04981 0.03974 -0.0454 1.0000 0.2644
-11.250 -0.8946 0.04663 0.03634 -0.0403 1.0000 0.2694
-11.000 -0.8624 0.04692 0.03679 -0.0399 1.0000 0.2757
-10.750 -0.8696 0.04549 0.03532 -0.0365 1.0000 0.2817
-10.500 -0.8982 0.04341 0.03307 -0.0307 1.0000 0.2871
-10.250 -0.8756 0.04335 0.03313 -0.0296 1.0000 0.2934
-10.000 -0.8827 0.04232 0.03207 -0.0254 1.0000 0.2993
-9.750 -0.9067 0.04091 0.03051 -0.0191 1.0000 0.3047
-9.500 -0.8904 0.04069 0.03040 -0.0172 1.0000 0.3106
-9.250 -0.8969 0.03995 0.02963 -0.0126 1.0000 0.3164
-9.000 -0.9180 0.03898 0.02854 -0.0059 1.0000 0.3218
-8.750 -0.9085 0.03868 0.02832 -0.0031 1.0000 0.3277
-8.500 -0.9146 0.03814 0.02776 0.0018 1.0000 0.3338
-8.250 -0.9277 0.03732 0.02684 0.0076 1.0000 0.3404
-8.000 -0.9174 0.03707 0.02668 0.0102 1.0000 0.3470
-7.750 -0.9210 0.03646 0.02601 0.0147 1.0000 0.3544
-7.500 -0.9187 0.03601 0.02557 0.0184 1.0000 0.3619
-7.250 -0.9175 0.03560 0.02515 0.0223 0.9998 0.3712
-7.000 -0.8858 0.03537 0.02495 0.0206 0.9923 0.3844
-6.750 -0.8597 0.03499 0.02454 0.0199 0.9839 0.3984
-6.500 -0.8337 0.03463 0.02410 0.0192 0.9757 0.4128
-6.250 -0.7985 0.03455 0.02410 0.0175 0.9680 0.4254
-6.000 -0.7689 0.03425 0.02379 0.0165 0.9598 0.4381
-5.750 -0.7411 0.03384 0.02329 0.0156 0.9512 0.4521
-5.500 -0.7090 0.03377 0.02328 0.0147 0.9425 0.4646
-5.250 -0.6744 0.03363 0.02314 0.0131 0.9346 0.4788
-5.000 -0.6529 0.03333 0.02279 0.0137 0.9241 0.4925
-4.750 -0.6182 0.03314 0.02256 0.0121 0.9164 0.5074
-4.500 -0.5910 0.03311 0.02258 0.0121 0.9059 0.5192
-4.250 -0.5540 0.03296 0.02240 0.0103 0.8986 0.5339
-4.000 -0.5410 0.03263 0.02201 0.0125 0.8862 0.5479
-3.750 -0.4939 0.03270 0.02212 0.0093 0.8801 0.5615
-3.500 -0.4737 0.03263 0.02205 0.0106 0.8681 0.5736
-3.250 -0.4373 0.03234 0.02170 0.0089 0.8613 0.5883
-3.000 -0.4114 0.03249 0.02190 0.0095 0.8495 0.5991
-2.750 -0.3693 0.03236 0.02176 0.0071 0.8431 0.6124
-2.500 -0.3556 0.03225 0.02163 0.0096 0.8306 0.6254
-2.250 -0.3032 0.03244 0.02187 0.0058 0.8248 0.6370
-2.000 -0.2809 0.03250 0.02194 0.0070 0.8139 0.6504
-1.750 -0.2485 0.03248 0.02191 0.0066 0.8057 0.6661
-1.500 -0.1802 0.03295 0.02244 0.0007 0.8018 0.6786
-1.250 -0.1658 0.03327 0.02279 0.0033 0.7883 0.6907
-1.000 -0.1257 0.03304 0.02253 0.0015 0.7823 0.7046
-0.750 -0.0956 0.03354 0.02307 0.0015 0.7699 0.7121
-0.500 -0.0624 0.03314 0.02263 0.0007 0.7631 0.7243
-0.250 -0.0315 0.03355 0.02308 0.0004 0.7509 0.7317
0.000 -0.0001 0.03316 0.02265 0.0000 0.7437 0.7437
0.250 0.0313 0.03355 0.02308 -0.0004 0.7317 0.7509
0.500 0.0621 0.03314 0.02263 -0.0007 0.7243 0.7631
0.750 0.0955 0.03353 0.02307 -0.0015 0.7122 0.7699
1.000 0.1253 0.03303 0.02253 -0.0015 0.7046 0.7823
1.250 0.1655 0.03328 0.02280 -0.0032 0.6907 0.7883
1.500 0.1805 0.03295 0.02244 -0.0007 0.6786 0.8018
1.750 0.2486 0.03247 0.02190 -0.0066 0.6660 0.8057
2.000 0.2806 0.03251 0.02195 -0.0070 0.6505 0.8140
2.250 0.3031 0.03244 0.02187 -0.0058 0.6370 0.8248
2.500 0.3557 0.03225 0.02162 -0.0096 0.6255 0.8306
2.750 0.3692 0.03237 0.02177 -0.0071 0.6125 0.8431
3.000 0.4114 0.03249 0.02190 -0.0095 0.5992 0.8496
3.250 0.4372 0.03233 0.02170 -0.0089 0.5883 0.8613
3.500 0.4738 0.03262 0.02204 -0.0106 0.5735 0.8681
3.750 0.4940 0.03270 0.02211 -0.0093 0.5615 0.8801
4.000 0.5409 0.03263 0.02201 -0.0125 0.5479 0.8862
4.250 0.5541 0.03295 0.02239 -0.0103 0.5338 0.8986
4.500 0.5911 0.03310 0.02257 -0.0122 0.5192 0.9060
4.750 0.6184 0.03313 0.02256 -0.0121 0.5072 0.9165
5.000 0.6531 0.03332 0.02279 -0.0137 0.4926 0.9242
5.250 0.6747 0.03362 0.02313 -0.0131 0.4787 0.9347
5.500 0.7092 0.03376 0.02327 -0.0147 0.4647 0.9426
5.750 0.7414 0.03383 0.02328 -0.0157 0.4521 0.9513
6.000 0.7691 0.03424 0.02378 -0.0165 0.4381 0.9599
6.250 0.7987 0.03454 0.02409 -0.0175 0.4253 0.9681
6.500 0.8337 0.03462 0.02410 -0.0192 0.4127 0.9758
6.750 0.8601 0.03497 0.02451 -0.0200 0.3982 0.9840
7.000 0.8862 0.03536 0.02493 -0.0207 0.3843 0.9924
7.250 0.9180 0.03559 0.02514 -0.0224 0.3711 0.9999
7.500 0.9190 0.03601 0.02557 -0.0185 0.3621 1.0000
7.750 0.9212 0.03645 0.02599 -0.0147 0.3544 1.0000
8.000 0.9175 0.03706 0.02666 -0.0102 0.3469 1.0000
8.250 0.9278 0.03732 0.02683 -0.0076 0.3404 1.0000
8.500 0.9151 0.03813 0.02775 -0.0019 0.3339 1.0000
8.750 0.9090 0.03867 0.02831 0.0030 0.3277 1.0000
9.000 0.9178 0.03897 0.02853 0.0059 0.3217 1.0000
9.250 0.8973 0.03994 0.02961 0.0125 0.3164 1.0000
9.500 0.8908 0.04067 0.03037 0.0172 0.3106 1.0000
9.750 0.9071 0.04089 0.03048 0.0190 0.3046 1.0000
10.000 0.8831 0.04230 0.03204 0.0253 0.2993 1.0000
10.250 0.8763 0.04332 0.03310 0.0295 0.2934 1.0000
10.500 0.8980 0.04340 0.03305 0.0307 0.2870 1.0000
10.750 0.8704 0.04546 0.03528 0.0364 0.2817 1.0000
11.000 0.8632 0.04686 0.03673 0.0399 0.2756 1.0000
11.250 0.8946 0.04662 0.03634 0.0403 0.2694 1.0000
11.500 0.8578 0.04978 0.03971 0.0453 0.2643 1.0000
11.750 0.8419 0.05223 0.04225 0.0483 0.2586 1.0000
12.000 0.8775 0.05154 0.04144 0.0489 0.2524 1.0000
12.250 0.8367 0.05592 0.04599 0.0524 0.2474 1.0000
12.500 0.7870 0.06196 0.05219 0.0544 0.2412 1.0000
12.750 0.8385 0.05914 0.04923 0.0556 0.2348 1.0000
13.000 0.7444 0.07068 0.06102 0.0558 0.2288 1.0000
13.250 0.6747 0.08211 0.07255 0.0534 0.2195 1.0000
13.500 0.7742 0.07139 0.06169 0.0582 0.2165 1.0000
13.750 0.6119 0.09707 0.08754 0.0497 0.2022 1.0000
14.000 0.6537 0.09288 0.08335 0.0527 0.1996 1.0000
14.500 0.6064 0.10648 0.09699 0.0488 0.1838 1.0000
15.000 0.5766 0.11794 0.10847 0.0454 0.1701 1.0000
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