GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Reynolds number: 500,000 Max Cl/Cd: 98.98 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe274-il-500000.txt Download as CSV file: xf-goe274-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 274 (DAIMLER V) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3367 0.10204 0.09985 -0.0214 1.0000 0.0183
-8.250 -0.3420 0.10022 0.09807 -0.0197 1.0000 0.0185
-8.000 -0.3494 0.09855 0.09643 -0.0176 1.0000 0.0188
-7.750 -0.3474 0.09591 0.09382 -0.0184 0.9989 0.0193
-7.500 -0.3312 0.09187 0.08978 -0.0238 0.9957 0.0202
-7.250 -0.2969 0.08558 0.08345 -0.0413 0.9899 0.0208
-7.000 -0.2634 0.07934 0.07715 -0.0538 0.9864 0.0208
-6.750 -0.2479 0.07471 0.07253 -0.0549 0.9849 0.0211
-6.500 -0.2252 0.07108 0.06889 -0.0577 0.9837 0.0213
-6.250 -0.2034 0.06760 0.06538 -0.0615 0.9793 0.0217
-6.000 -0.1741 0.06364 0.06139 -0.0676 0.9760 0.0223
-5.750 -0.1385 0.05929 0.05697 -0.0752 0.9737 0.0235
-5.500 -0.0726 0.05252 0.04989 -0.0912 0.9719 0.0252
-5.250 -0.0326 0.04672 0.04389 -0.0984 0.9709 0.0254
-5.000 -0.0128 0.04349 0.04068 -0.0998 0.9657 0.0257
-4.750 0.0170 0.04081 0.03796 -0.1028 0.9628 0.0262
-4.500 0.0514 0.03803 0.03509 -0.1065 0.9602 0.0270
-4.250 0.0886 0.03503 0.03195 -0.1103 0.9578 0.0282
-4.000 0.1313 0.03277 0.02924 -0.1125 0.9528 0.0306
-3.750 0.1636 0.03066 0.02684 -0.1139 0.9474 0.0308
-3.500 0.1915 0.02635 0.02250 -0.1163 0.9435 0.0315
-3.250 0.2170 0.02472 0.02083 -0.1168 0.9364 0.0321
-3.000 0.2456 0.02316 0.01916 -0.1176 0.9300 0.0330
-2.750 0.2743 0.02169 0.01754 -0.1179 0.9220 0.0344
-2.500 0.3074 0.02167 0.01710 -0.1172 0.9131 0.0374
-2.250 0.3359 0.01883 0.01400 -0.1179 0.9013 0.0383
-2.000 0.3629 0.01735 0.01249 -0.1181 0.8879 0.0392
-1.750 0.3906 0.01638 0.01142 -0.1182 0.8730 0.0405
-1.500 0.4189 0.01565 0.01053 -0.1181 0.8558 0.0430
-1.250 0.4479 0.01653 0.01107 -0.1172 0.8351 0.0459
-1.000 0.4760 0.01402 0.00842 -0.1178 0.8116 0.0484
-0.750 0.5029 0.01346 0.00768 -0.1175 0.7793 0.0508
-0.500 0.5292 0.01416 0.00804 -0.1165 0.7342 0.0559
1.000 0.1235 0.05320 0.04814 -0.0084 0.5734 0.0460
1.250 0.7146 0.01176 0.00400 -0.1136 0.4742 0.0474
1.500 0.7422 0.01179 0.00397 -0.1135 0.4608 0.0457
1.750 0.7701 0.01155 0.00371 -0.1135 0.4482 0.0452
2.000 0.7978 0.01150 0.00360 -0.1135 0.4351 0.0455
2.250 0.8253 0.01150 0.00355 -0.1135 0.4222 0.0459
2.500 0.8533 0.01140 0.00342 -0.1136 0.4103 0.0484
2.750 0.8811 0.01142 0.00342 -0.1137 0.3997 0.0498
3.000 0.9086 0.01150 0.00344 -0.1136 0.3897 0.0516
3.250 0.9358 0.01160 0.00349 -0.1135 0.3792 0.0550
3.500 0.9633 0.01168 0.00357 -0.1134 0.3690 0.0666
3.750 0.9826 0.01017 0.00384 -0.1120 0.3602 1.0000
4.000 1.0095 0.01036 0.00396 -0.1119 0.3492 1.0000
4.250 1.0364 0.01055 0.00409 -0.1117 0.3378 1.0000
4.500 1.0630 0.01077 0.00426 -0.1116 0.3260 1.0000
4.750 1.0894 0.01101 0.00444 -0.1114 0.3127 1.0000
5.000 1.1155 0.01127 0.00463 -0.1112 0.2979 1.0000
5.250 1.1413 0.01155 0.00485 -0.1109 0.2809 1.0000
5.500 1.1663 0.01192 0.00509 -0.1105 0.2592 1.0000
5.750 1.1913 0.01229 0.00535 -0.1102 0.2396 1.0000
6.000 1.2162 0.01265 0.00564 -0.1098 0.2243 1.0000
6.250 1.2408 0.01303 0.00596 -0.1093 0.2106 1.0000
6.500 1.2652 0.01343 0.00629 -0.1089 0.1995 1.0000
6.750 1.2902 0.01374 0.00660 -0.1085 0.1917 1.0000
7.000 1.3144 0.01412 0.00695 -0.1080 0.1835 1.0000
7.250 1.3387 0.01449 0.00730 -0.1076 0.1748 1.0000
7.500 1.3627 0.01485 0.00766 -0.1071 0.1652 1.0000
7.750 1.3862 0.01527 0.00805 -0.1065 0.1542 1.0000
8.000 1.4090 0.01575 0.00844 -0.1058 0.1331 1.0000
8.250 1.4211 0.01734 0.00954 -0.1036 0.0682 1.0000
8.500 1.4324 0.01895 0.01088 -0.1011 0.0244 1.0000
8.750 1.4510 0.01975 0.01174 -0.0996 0.0212 1.0000
9.000 1.4704 0.02041 0.01251 -0.0983 0.0199 1.0000
9.250 1.4884 0.02115 0.01335 -0.0967 0.0188 1.0000
9.500 1.5042 0.02201 0.01431 -0.0949 0.0177 1.0000
9.750 1.5155 0.02315 0.01555 -0.0923 0.0167 1.0000
10.000 1.5220 0.02447 0.01701 -0.0890 0.0160 1.0000
10.250 1.5314 0.02537 0.01800 -0.0861 0.0156 1.0000
10.500 1.5389 0.02643 0.01917 -0.0830 0.0153 1.0000
10.750 1.5447 0.02766 0.02051 -0.0799 0.0149 1.0000
11.000 1.5490 0.02904 0.02200 -0.0768 0.0145 1.0000
11.250 1.5519 0.03058 0.02365 -0.0738 0.0142 1.0000
11.500 1.5533 0.03231 0.02549 -0.0709 0.0139 1.0000
11.750 1.5532 0.03425 0.02754 -0.0682 0.0136 1.0000
12.000 1.5517 0.03645 0.02984 -0.0657 0.0133 1.0000
12.250 1.5474 0.03905 0.03255 -0.0634 0.0130 1.0000
12.500 1.5402 0.04215 0.03576 -0.0615 0.0128 1.0000
12.750 1.5295 0.04584 0.03956 -0.0599 0.0126 1.0000
13.000 1.5164 0.05005 0.04388 -0.0586 0.0124 1.0000
13.250 1.5090 0.05382 0.04776 -0.0579 0.0122 1.0000
13.500 1.5082 0.05705 0.05112 -0.0578 0.0121 1.0000
13.750 1.5061 0.06057 0.05476 -0.0580 0.0119 1.0000
14.000 1.5029 0.06431 0.05862 -0.0582 0.0118 1.0000
14.250 1.4995 0.06817 0.06259 -0.0586 0.0117 1.0000
14.500 1.4959 0.07209 0.06663 -0.0591 0.0116 1.0000
14.750 1.4924 0.07605 0.07069 -0.0596 0.0114 1.0000
15.000 1.4889 0.08000 0.07476 -0.0602 0.0113 1.0000
15.250 1.4856 0.08393 0.07880 -0.0607 0.0112 1.0000
15.500 1.4821 0.08793 0.08290 -0.0614 0.0111 1.0000
15.750 1.4789 0.09190 0.08698 -0.0621 0.0110 1.0000
16.000 1.4756 0.09591 0.09110 -0.0628 0.0109 1.0000
16.250 1.4720 0.10001 0.09531 -0.0637 0.0108 1.0000
16.500 1.4682 0.10418 0.09959 -0.0647 0.0107 1.0000
16.750 1.4641 0.10848 0.10401 -0.0659 0.0106 1.0000
17.000 1.4595 0.11294 0.10860 -0.0673 0.0106 1.0000
17.250 1.4546 0.11758 0.11336 -0.0691 0.0105 1.0000
17.500 1.4490 0.12238 0.11829 -0.0711 0.0104 1.0000
17.750 1.4434 0.12730 0.12333 -0.0733 0.0103 1.0000
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