GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Reynolds number: 500,000 Max Cl/Cd: 94.35 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe275-il-500000-n5.txt Download as CSV file: xf-goe275-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 275 (DAIMLER VI) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3269 0.10320 0.10090 -0.0235 1.0000 0.0100
-9.000 -0.3244 0.10081 0.09853 -0.0234 1.0000 0.0097
-8.750 -0.3222 0.09863 0.09638 -0.0232 1.0000 0.0106
-8.500 -0.3205 0.09666 0.09445 -0.0227 1.0000 0.0111
-8.250 -0.3125 0.09222 0.09002 -0.0261 0.9985 0.0105
-8.000 -0.2964 0.08804 0.08584 -0.0309 0.9953 0.0106
-7.750 -0.2804 0.08465 0.08246 -0.0350 0.9909 0.0109
-7.500 -0.2641 0.08064 0.07845 -0.0401 0.9858 0.0110
-7.000 -0.2297 0.07238 0.07018 -0.0507 0.9672 0.0114
-6.750 -0.2102 0.06800 0.06579 -0.0566 0.9564 0.0120
-6.500 -0.1833 0.06236 0.06009 -0.0654 0.9476 0.0129
-6.250 -0.1535 0.05839 0.05607 -0.0720 0.9409 0.0132
-6.000 -0.1176 0.05412 0.05173 -0.0798 0.9350 0.0137
-5.750 -0.0800 0.04933 0.04683 -0.0879 0.9274 0.0143
-5.500 -0.0388 0.04334 0.04064 -0.0969 0.9183 0.0158
-5.000 0.0265 0.03734 0.03433 -0.1047 0.8943 0.0170
-4.750 0.0571 0.03218 0.02880 -0.1076 0.8813 0.0185
-4.500 0.0808 0.03081 0.02732 -0.1082 0.8678 0.0193
-4.250 0.1051 0.02919 0.02557 -0.1086 0.8555 0.0200
-4.000 0.1302 0.02672 0.02286 -0.1089 0.8438 0.0204
-3.750 0.1584 0.02291 0.01845 -0.1082 0.8318 0.0225
-3.500 0.1806 0.02211 0.01767 -0.1082 0.8168 0.0231
-3.250 0.2042 0.02136 0.01681 -0.1079 0.7990 0.0241
-3.000 0.2284 0.01967 0.01481 -0.1071 0.7752 0.0241
-2.750 0.2515 0.01837 0.01316 -0.1060 0.7391 0.0243
-2.500 0.2731 0.01741 0.01178 -0.1045 0.6906 0.0246
-2.250 0.2949 0.01670 0.01066 -0.1030 0.6438 0.0256
-2.000 0.3180 0.01585 0.00946 -0.1018 0.6100 0.0256
-1.750 0.3422 0.01510 0.00842 -0.1008 0.5825 0.0257
-1.500 0.3668 0.01448 0.00753 -0.1000 0.5570 0.0260
-1.250 0.3916 0.01396 0.00677 -0.0991 0.5326 0.0261
-1.000 0.4169 0.01388 0.00643 -0.0983 0.5070 0.0268
-0.750 0.4416 0.01341 0.00573 -0.0976 0.4808 0.0272
-0.500 0.4663 0.01310 0.00524 -0.0968 0.4535 0.0271
-0.250 0.4910 0.01270 0.00468 -0.0961 0.4281 0.0272
0.000 0.5157 0.01233 0.00419 -0.0954 0.4062 0.0274
0.250 0.5405 0.01206 0.00383 -0.0948 0.3872 0.0278
0.500 0.5656 0.01190 0.00358 -0.0942 0.3712 0.0281
0.750 0.5907 0.01177 0.00340 -0.0936 0.3591 0.0285
1.000 0.6164 0.01164 0.00325 -0.0931 0.3507 0.0290
1.250 0.6418 0.01158 0.00315 -0.0925 0.3424 0.0298
1.500 0.6675 0.01152 0.00306 -0.0920 0.3335 0.0304
1.750 0.6929 0.01147 0.00297 -0.0915 0.3257 0.0306
2.000 0.7187 0.01142 0.00291 -0.0910 0.3185 0.0307
2.250 0.7441 0.01143 0.00288 -0.0905 0.3115 0.0312
2.500 0.7702 0.01142 0.00286 -0.0900 0.3062 0.0317
2.750 0.7960 0.01144 0.00288 -0.0896 0.3003 0.0323
3.250 0.8478 0.01152 0.00293 -0.0887 0.2899 0.0338
3.500 0.8736 0.01157 0.00298 -0.0883 0.2845 0.0363
3.750 0.8992 0.01168 0.00306 -0.0878 0.2786 0.0376
4.000 0.9251 0.01176 0.00315 -0.0874 0.2725 0.0390
4.500 0.9811 0.01047 0.00363 -0.0881 0.2532 1.0000
4.750 1.0060 0.01067 0.00377 -0.0875 0.2409 1.0000
5.000 1.0303 0.01092 0.00393 -0.0868 0.2237 1.0000
5.250 1.0536 0.01127 0.00414 -0.0860 0.1992 1.0000
5.500 1.0766 0.01164 0.00441 -0.0852 0.1827 1.0000
5.750 1.1000 0.01197 0.00468 -0.0845 0.1725 1.0000
6.000 1.1235 0.01229 0.00496 -0.0837 0.1650 1.0000
6.250 1.1474 0.01257 0.00523 -0.0830 0.1586 1.0000
6.500 1.1706 0.01290 0.00555 -0.0822 0.1523 1.0000
6.750 1.1946 0.01315 0.00582 -0.0816 0.1475 1.0000
7.000 1.2180 0.01344 0.00612 -0.0808 0.1402 1.0000
7.250 1.2411 0.01376 0.00644 -0.0801 0.1323 1.0000
7.750 1.2820 0.01487 0.00730 -0.0778 0.0907 1.0000
8.000 1.3034 0.01531 0.00774 -0.0768 0.0852 1.0000
8.250 1.3241 0.01579 0.00823 -0.0757 0.0808 1.0000
8.500 1.3439 0.01632 0.00877 -0.0745 0.0759 1.0000
8.750 1.3651 0.01671 0.00921 -0.0735 0.0737 1.0000
9.000 1.3864 0.01706 0.00962 -0.0725 0.0713 1.0000
9.250 1.4067 0.01748 0.01010 -0.0713 0.0685 1.0000
9.500 1.4257 0.01797 0.01062 -0.0700 0.0656 1.0000
9.750 1.4437 0.01852 0.01121 -0.0686 0.0628 1.0000
10.000 1.4631 0.01890 0.01166 -0.0673 0.0608 1.0000
10.250 1.4813 0.01929 0.01212 -0.0658 0.0581 1.0000
10.500 1.4972 0.01980 0.01264 -0.0640 0.0535 1.0000
10.750 1.5122 0.02034 0.01320 -0.0621 0.0488 1.0000
11.000 1.5245 0.02105 0.01385 -0.0599 0.0388 1.0000
11.500 1.5304 0.02364 0.01631 -0.0531 0.0150 1.0000
11.750 1.5382 0.02463 0.01739 -0.0506 0.0130 1.0000
12.000 1.5463 0.02564 0.01849 -0.0482 0.0119 1.0000
12.250 1.5524 0.02681 0.01975 -0.0458 0.0110 1.0000
12.500 1.5564 0.02818 0.02122 -0.0433 0.0102 1.0000
12.750 1.5629 0.02942 0.02257 -0.0413 0.0098 1.0000
13.000 1.5679 0.03083 0.02410 -0.0394 0.0093 1.0000
13.250 1.5712 0.03244 0.02582 -0.0376 0.0089 1.0000
13.500 1.5736 0.03422 0.02771 -0.0359 0.0086 1.0000
13.750 1.5737 0.03630 0.02990 -0.0345 0.0082 1.0000
14.000 1.5711 0.03879 0.03251 -0.0332 0.0078 1.0000
14.250 1.5654 0.04181 0.03567 -0.0323 0.0076 1.0000
14.500 1.5617 0.04484 0.03882 -0.0320 0.0073 1.0000
14.750 1.5583 0.04805 0.04217 -0.0320 0.0072 1.0000
15.000 1.5514 0.05194 0.04621 -0.0325 0.0070 1.0000
15.250 1.5440 0.05615 0.05055 -0.0335 0.0069 1.0000
15.500 1.5344 0.06089 0.05544 -0.0348 0.0067 1.0000
15.750 1.5232 0.06609 0.06079 -0.0366 0.0066 1.0000
16.000 1.5101 0.07181 0.06666 -0.0387 0.0066 1.0000
16.250 1.4957 0.07793 0.07293 -0.0412 0.0065 1.0000
16.500 1.4808 0.08429 0.07944 -0.0439 0.0064 1.0000
16.750 1.4647 0.09102 0.08631 -0.0469 0.0064 1.0000
17.000 1.4494 0.09770 0.09312 -0.0499 0.0064 1.0000
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