GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 200,000 Max Cl/Cd: 77.39 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe282-il-200000.txt Download as CSV file: xf-goe282-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 282 (DAIMLER XIII) 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3487 0.09421 0.09107 -0.0215 1.0000 0.0462
-7.250 -0.3610 0.09278 0.08971 -0.0188 1.0000 0.0468
-7.000 -0.3680 0.09076 0.08775 -0.0177 1.0000 0.0478
-6.750 -0.3734 0.08850 0.08554 -0.0173 1.0000 0.0490
-6.500 -0.3773 0.08597 0.08305 -0.0182 1.0000 0.0505
-6.250 -0.3282 0.07836 0.07528 -0.0427 0.9945 0.0534
-6.000 -0.3189 0.07266 0.06963 -0.0419 0.9911 0.0550
-5.750 -0.2946 0.06983 0.06679 -0.0431 0.9871 0.0571
-5.500 -0.2347 0.06107 0.05772 -0.0637 0.9815 0.0666
-5.250 -0.2168 0.05875 0.05547 -0.0623 0.9766 0.0686
-5.000 -0.1603 0.05211 0.04844 -0.0762 0.9724 0.0795
-4.750 -0.1368 0.04971 0.04613 -0.0764 0.9681 0.0816
-4.500 -0.0939 0.04544 0.04159 -0.0835 0.9622 0.0935
-4.250 -0.0396 0.03048 0.02558 -0.0942 0.9603 0.0638
-4.000 0.0052 0.02452 0.01877 -0.0992 0.9585 0.0631
-3.750 0.0460 0.02144 0.01504 -0.1020 0.9549 0.0636
-3.500 0.0834 0.02017 0.01334 -0.1037 0.9487 0.0659
-3.250 0.1257 0.01808 0.01095 -0.1067 0.9458 0.0680
-3.000 0.1704 0.01700 0.00981 -0.1100 0.9434 0.0716
-2.750 0.2050 0.01630 0.00901 -0.1111 0.9354 0.0759
-2.500 0.2476 0.01534 0.00797 -0.1137 0.9315 0.0797
-2.250 0.2885 0.01456 0.00724 -0.1160 0.9272 0.0867
-2.000 0.3217 0.01401 0.00674 -0.1167 0.9178 0.0979
-1.750 0.3572 0.01351 0.00634 -0.1176 0.9095 0.1259
-1.500 0.3925 0.01327 0.00610 -0.1185 0.8999 0.1686
-1.250 0.4227 0.01307 0.00586 -0.1184 0.8860 0.1882
-1.000 0.4523 0.01282 0.00556 -0.1181 0.8704 0.2035
-0.750 0.4799 0.01257 0.00529 -0.1175 0.8510 0.2166
-0.500 0.5076 0.01231 0.00498 -0.1169 0.8290 0.2288
-0.250 0.5352 0.01210 0.00472 -0.1164 0.8057 0.2437
0.000 0.5630 0.01192 0.00446 -0.1159 0.7834 0.2565
0.250 0.5905 0.01181 0.00427 -0.1155 0.7610 0.2680
0.500 0.6178 0.01171 0.00411 -0.1151 0.7391 0.2830
0.750 0.6446 0.01161 0.00402 -0.1147 0.7178 0.3050
1.000 0.6695 0.01094 0.00405 -0.1143 0.6980 0.5450
1.250 0.6925 0.01019 0.00394 -0.1124 0.6800 1.0000
1.500 0.7193 0.01041 0.00397 -0.1120 0.6628 1.0000
1.750 0.7461 0.01062 0.00402 -0.1116 0.6463 1.0000
2.000 0.7727 0.01082 0.00410 -0.1112 0.6303 1.0000
2.250 0.7993 0.01103 0.00420 -0.1108 0.6148 1.0000
2.500 0.8258 0.01125 0.00431 -0.1104 0.5998 1.0000
2.750 0.8521 0.01148 0.00444 -0.1100 0.5848 1.0000
3.000 0.8782 0.01172 0.00458 -0.1096 0.5697 1.0000
3.250 0.9042 0.01198 0.00476 -0.1092 0.5546 1.0000
3.500 0.9301 0.01225 0.00496 -0.1087 0.5396 1.0000
3.750 0.9558 0.01253 0.00517 -0.1083 0.5245 1.0000
4.000 0.9812 0.01281 0.00541 -0.1077 0.5079 1.0000
4.250 1.0059 0.01308 0.00562 -0.1071 0.4883 1.0000
4.500 1.0300 0.01337 0.00583 -0.1063 0.4676 1.0000
4.750 1.0540 0.01362 0.00605 -0.1055 0.4438 1.0000
5.000 1.0774 0.01394 0.00629 -0.1047 0.4204 1.0000
5.250 1.1006 0.01428 0.00655 -0.1038 0.3955 1.0000
5.500 1.1234 0.01468 0.00685 -0.1030 0.3718 1.0000
5.750 1.1457 0.01513 0.00718 -0.1020 0.3505 1.0000
6.000 1.1680 0.01559 0.00757 -0.1012 0.3308 1.0000
6.250 1.1903 0.01605 0.00795 -0.1003 0.3120 1.0000
6.500 1.2123 0.01652 0.00836 -0.0994 0.2950 1.0000
6.750 1.2346 0.01697 0.00880 -0.0985 0.2811 1.0000
7.000 1.2566 0.01743 0.00924 -0.0976 0.2669 1.0000
7.250 1.2777 0.01791 0.00968 -0.0967 0.2504 1.0000
7.500 1.2977 0.01845 0.01015 -0.0955 0.2320 1.0000
7.750 1.3186 0.01894 0.01061 -0.0945 0.2160 1.0000
8.000 1.3396 0.01940 0.01109 -0.0935 0.1973 1.0000
8.250 1.3591 0.01998 0.01158 -0.0923 0.1703 1.0000
8.500 1.3729 0.02101 0.01229 -0.0904 0.1221 1.0000
8.750 1.3850 0.02219 0.01326 -0.0881 0.0959 1.0000
9.000 1.3984 0.02320 0.01420 -0.0860 0.0818 1.0000
9.250 1.4130 0.02404 0.01507 -0.0841 0.0728 1.0000
9.500 1.4270 0.02478 0.01585 -0.0819 0.0645 1.0000
9.750 1.4392 0.02564 0.01672 -0.0796 0.0548 1.0000
10.250 1.4484 0.02851 0.01940 -0.0733 0.0244 1.0000
10.500 1.4550 0.02984 0.02083 -0.0706 0.0230 1.0000
10.750 1.4618 0.03121 0.02235 -0.0681 0.0220 1.0000
11.000 1.4678 0.03268 0.02397 -0.0658 0.0214 1.0000
11.250 1.4725 0.03432 0.02578 -0.0634 0.0209 1.0000
11.500 1.4757 0.03615 0.02777 -0.0612 0.0207 1.0000
11.750 1.4775 0.03819 0.02999 -0.0592 0.0205 1.0000
12.000 1.4775 0.04051 0.03249 -0.0574 0.0203 1.0000
12.250 1.4755 0.04316 0.03532 -0.0558 0.0201 1.0000
12.500 1.4717 0.04616 0.03849 -0.0546 0.0199 1.0000
12.750 1.4664 0.04952 0.04202 -0.0538 0.0196 1.0000
13.000 1.4596 0.05326 0.04593 -0.0534 0.0194 1.0000
13.250 1.4521 0.05724 0.05007 -0.0533 0.0192 1.0000
13.500 1.4437 0.06151 0.05450 -0.0535 0.0190 1.0000
13.750 1.4350 0.06596 0.05911 -0.0539 0.0188 1.0000
14.000 1.4266 0.07050 0.06379 -0.0545 0.0187 1.0000
14.250 1.4189 0.07501 0.06842 -0.0552 0.0186 1.0000
14.500 1.4119 0.07946 0.07299 -0.0559 0.0186 1.0000
14.750 1.4060 0.08374 0.07739 -0.0565 0.0186 1.0000
15.000 1.4011 0.08787 0.08162 -0.0571 0.0186 1.0000
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Polar data table (+)
Polar graphs
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