GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Reynolds number: 200,000 Max Cl/Cd: 71.09 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe255-il-200000-n5.txt Download as CSV file: xf-goe255-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 255 (MVA CA.6) 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4959 0.11039 0.10626 -0.0678 1.0000 0.0155
-15.750 -0.5258 0.10061 0.09630 -0.0728 1.0000 0.0154
-15.500 -0.5459 0.09326 0.08880 -0.0766 1.0000 0.0154
-15.250 -0.5620 0.08706 0.08248 -0.0797 1.0000 0.0154
-15.000 -0.5761 0.08166 0.07697 -0.0821 1.0000 0.0155
-14.750 -0.5893 0.07690 0.07211 -0.0840 1.0000 0.0156
-14.500 -0.6027 0.07269 0.06781 -0.0853 1.0000 0.0156
-14.250 -0.6162 0.06886 0.06390 -0.0860 1.0000 0.0157
-14.000 -0.6300 0.06534 0.06031 -0.0864 1.0000 0.0158
-13.750 -0.6267 0.06077 0.05558 -0.0910 0.9956 0.0160
-13.500 -0.6208 0.05649 0.05116 -0.0957 0.9906 0.0162
-13.250 -0.6129 0.05253 0.04705 -0.1001 0.9849 0.0165
-13.000 -0.6051 0.04889 0.04325 -0.1041 0.9773 0.0168
-12.750 -0.5967 0.04543 0.03969 -0.1077 0.9691 0.0172
-12.500 -0.5882 0.04204 0.03624 -0.1115 0.9596 0.0176
-12.250 -0.5820 0.03896 0.03307 -0.1142 0.9462 0.0180
-12.000 -0.5773 0.03615 0.03014 -0.1162 0.9298 0.0184
-11.750 -0.5748 0.03358 0.02745 -0.1175 0.9082 0.0189
-11.500 -0.5710 0.03128 0.02499 -0.1184 0.8854 0.0193
-11.250 -0.5672 0.02956 0.02309 -0.1176 0.8647 0.0198
-11.000 -0.5583 0.02814 0.02146 -0.1168 0.8489 0.0204
-10.750 -0.5459 0.02690 0.02002 -0.1160 0.8364 0.0209
-10.250 -0.5186 0.02453 0.01735 -0.1147 0.8161 0.0225
-10.000 -0.5007 0.02361 0.01628 -0.1141 0.8082 0.0237
-9.750 -0.4812 0.02281 0.01532 -0.1136 0.8003 0.0253
-9.500 -0.4619 0.02192 0.01431 -0.1132 0.7936 0.0271
-9.250 -0.4410 0.02116 0.01344 -0.1128 0.7871 0.0295
-9.000 -0.4195 0.02040 0.01259 -0.1124 0.7808 0.0326
-8.750 -0.3971 0.01971 0.01180 -0.1121 0.7754 0.0377
-8.500 -0.3747 0.01898 0.01109 -0.1118 0.7693 0.0472
-8.250 -0.3511 0.01838 0.01049 -0.1116 0.7637 0.0613
-8.000 -0.3262 0.01791 0.00994 -0.1115 0.7587 0.0745
-7.750 -0.3015 0.01742 0.00944 -0.1114 0.7526 0.0869
-7.500 -0.2765 0.01696 0.00897 -0.1113 0.7470 0.1005
-7.250 -0.2510 0.01654 0.00855 -0.1112 0.7419 0.1167
-7.000 -0.2252 0.01617 0.00822 -0.1112 0.7357 0.1368
-6.750 -0.1989 0.01586 0.00792 -0.1112 0.7301 0.1594
-6.500 -0.1723 0.01558 0.00763 -0.1113 0.7251 0.1803
-6.250 -0.1456 0.01531 0.00737 -0.1113 0.7192 0.1967
-6.000 -0.1186 0.01508 0.00708 -0.1113 0.7136 0.2103
-5.750 -0.0912 0.01487 0.00679 -0.1114 0.7089 0.2232
-5.500 -0.0642 0.01464 0.00658 -0.1114 0.7027 0.2375
-5.250 -0.0371 0.01443 0.00637 -0.1114 0.6970 0.2535
-5.000 -0.0095 0.01427 0.00619 -0.1115 0.6921 0.2716
-4.750 0.0178 0.01416 0.00614 -0.1115 0.6858 0.2935
-4.500 0.0458 0.01412 0.00607 -0.1116 0.6800 0.3161
-4.250 0.0741 0.01412 0.00600 -0.1117 0.6749 0.3346
-4.000 0.1021 0.01414 0.00599 -0.1118 0.6684 0.3512
-3.750 0.1305 0.01418 0.00593 -0.1119 0.6628 0.3654
-3.500 0.1587 0.01421 0.00587 -0.1120 0.6570 0.3764
-3.250 0.1866 0.01420 0.00582 -0.1120 0.6502 0.3847
-3.000 0.2148 0.01421 0.00570 -0.1121 0.6443 0.3929
-2.750 0.2426 0.01419 0.00564 -0.1121 0.6368 0.3991
-2.500 0.2705 0.01418 0.00555 -0.1122 0.6304 0.4051
-2.250 0.2986 0.01420 0.00547 -0.1123 0.6243 0.4119
-2.000 0.3263 0.01417 0.00543 -0.1123 0.6181 0.4173
-1.750 0.3543 0.01417 0.00535 -0.1124 0.6129 0.4229
-1.500 0.3822 0.01419 0.00532 -0.1125 0.6068 0.4282
-1.250 0.4100 0.01418 0.00529 -0.1126 0.6016 0.4331
-0.750 0.4658 0.01423 0.00526 -0.1128 0.5924 0.4443
-0.500 0.4935 0.01424 0.00527 -0.1129 0.5882 0.4507
-0.250 0.5213 0.01427 0.00529 -0.1130 0.5845 0.4582
0.000 0.5492 0.01432 0.00529 -0.1131 0.5809 0.4654
0.250 0.5764 0.01434 0.00536 -0.1132 0.5762 0.4719
0.500 0.6039 0.01439 0.00539 -0.1132 0.5717 0.4781
0.750 0.6315 0.01444 0.00541 -0.1133 0.5677 0.4827
1.000 0.6590 0.01448 0.00547 -0.1134 0.5640 0.4875
1.250 0.6862 0.01454 0.00557 -0.1134 0.5602 0.4934
1.500 0.7136 0.01461 0.00566 -0.1135 0.5567 0.5001
1.750 0.7408 0.01466 0.00575 -0.1135 0.5533 0.5078
2.250 0.7949 0.01481 0.00597 -0.1136 0.5463 0.5267
2.500 0.8215 0.01489 0.00613 -0.1136 0.5429 0.5394
2.750 0.8481 0.01495 0.00629 -0.1135 0.5395 0.5560
3.000 0.8746 0.01502 0.00643 -0.1135 0.5361 0.5786
3.250 0.9007 0.01507 0.00658 -0.1133 0.5321 0.6100
3.500 0.9247 0.01508 0.00680 -0.1127 0.5271 0.6540
3.750 0.9480 0.01506 0.00701 -0.1119 0.5229 0.7152
4.000 0.9699 0.01499 0.00718 -0.1106 0.5186 0.8038
4.250 1.0037 0.01492 0.00734 -0.1117 0.5137 1.0000
4.500 1.0279 0.01511 0.00756 -0.1113 0.5090 1.0000
4.750 1.0526 0.01531 0.00775 -0.1109 0.5044 1.0000
5.000 1.0778 0.01553 0.00791 -0.1106 0.4999 1.0000
5.250 1.1000 0.01574 0.00819 -0.1099 0.4940 1.0000
5.500 1.1224 0.01595 0.00841 -0.1091 0.4875 1.0000
5.750 1.1446 0.01618 0.00863 -0.1083 0.4810 1.0000
6.000 1.1646 0.01641 0.00892 -0.1071 0.4727 1.0000
6.250 1.1843 0.01666 0.00917 -0.1059 0.4645 1.0000
6.500 1.2021 0.01693 0.00947 -0.1043 0.4543 1.0000
6.750 1.2175 0.01721 0.00980 -0.1023 0.4433 1.0000
7.000 1.2318 0.01754 0.01015 -0.1002 0.4307 1.0000
7.250 1.2450 0.01796 0.01056 -0.0979 0.4140 1.0000
7.500 1.2545 0.01852 0.01105 -0.0952 0.3928 1.0000
7.750 1.2604 0.01930 0.01172 -0.0921 0.3732 1.0000
8.000 1.2663 0.02021 0.01253 -0.0892 0.3589 1.0000
8.250 1.2736 0.02118 0.01343 -0.0867 0.3483 1.0000
8.500 1.2832 0.02212 0.01435 -0.0846 0.3400 1.0000
8.750 1.2912 0.02320 0.01538 -0.0825 0.3320 1.0000
9.000 1.3016 0.02422 0.01640 -0.0808 0.3244 1.0000
9.250 1.3105 0.02537 0.01752 -0.0790 0.3168 1.0000
9.500 1.3207 0.02649 0.01864 -0.0775 0.3095 1.0000
9.750 1.3301 0.02770 0.01985 -0.0759 0.3017 1.0000
10.000 1.3393 0.02896 0.02110 -0.0745 0.2946 1.0000
10.250 1.3498 0.03017 0.02238 -0.0733 0.2869 1.0000
10.500 1.3571 0.03160 0.02378 -0.0718 0.2799 1.0000
10.750 1.3679 0.03287 0.02516 -0.0709 0.2717 1.0000
11.000 1.3740 0.03448 0.02676 -0.0695 0.2640 1.0000
11.250 1.3833 0.03592 0.02829 -0.0686 0.2543 1.0000
11.500 1.3885 0.03771 0.03012 -0.0675 0.2427 1.0000
11.750 1.3926 0.03966 0.03209 -0.0664 0.2293 1.0000
12.000 1.3959 0.04175 0.03418 -0.0654 0.2140 1.0000
12.250 1.3929 0.04443 0.03680 -0.0641 0.1937 1.0000
12.500 1.3847 0.04770 0.03995 -0.0628 0.1745 1.0000
12.750 1.3775 0.05097 0.04314 -0.0616 0.1593 1.0000
13.000 1.3717 0.05418 0.04631 -0.0606 0.1463 1.0000
13.250 1.3678 0.05731 0.04941 -0.0598 0.1339 1.0000
13.500 1.3621 0.06069 0.05274 -0.0590 0.1154 1.0000
13.750 1.3519 0.06468 0.05662 -0.0584 0.0936 1.0000
14.000 1.3382 0.06913 0.06095 -0.0578 0.0757 1.0000
14.250 1.3262 0.07351 0.06527 -0.0574 0.0553 1.0000
14.500 1.3033 0.07932 0.07090 -0.0570 0.0247 1.0000
14.750 1.2944 0.08357 0.07519 -0.0570 0.0203 1.0000
15.000 1.2915 0.08714 0.07885 -0.0570 0.0186 1.0000
15.250 1.2888 0.09073 0.08254 -0.0572 0.0175 1.0000
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