GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 500,000 Max Cl/Cd: 94.94 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe143-il-500000.txt Download as CSV file: xf-goe143-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 143 (MVA H.20) 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 -0.4211 0.09809 0.09585 -0.0053 1.0000 0.0250
-8.250 -0.4216 0.09405 0.09185 -0.0115 1.0000 0.0262
-8.000 -0.4192 0.09005 0.08788 -0.0156 1.0000 0.0263
-7.750 -0.4098 0.08559 0.08344 -0.0205 1.0000 0.0264
-7.500 -0.4032 0.07958 0.07744 -0.0258 1.0000 0.0266
-7.250 -0.3954 0.07671 0.07458 -0.0246 1.0000 0.0270
-7.000 -0.3835 0.07426 0.07213 -0.0251 1.0000 0.0275
-6.750 -0.3710 0.07147 0.06935 -0.0270 1.0000 0.0281
-6.500 -0.3586 0.06854 0.06642 -0.0294 1.0000 0.0294
-6.250 -0.3337 0.06234 0.06011 -0.0406 1.0000 0.0326
-6.000 -0.3217 0.05800 0.05570 -0.0430 1.0000 0.0327
-5.750 -0.2974 0.04982 0.04740 -0.0502 0.9969 0.0335
-5.500 -0.2678 0.04783 0.04539 -0.0529 0.9942 0.0343
-5.250 -0.2355 0.04559 0.04310 -0.0563 0.9902 0.0362
-5.000 -0.1801 0.04012 0.03714 -0.0647 0.9862 0.0407
-4.500 -0.1185 0.03123 0.02801 -0.0724 0.9757 0.0434
-4.250 -0.0844 0.02937 0.02603 -0.0748 0.9699 0.0456
-4.000 -0.0474 0.02883 0.02510 -0.0754 0.9590 0.0508
-3.750 -0.0206 0.02279 0.01860 -0.0776 0.9476 0.0525
-3.500 0.0052 0.02143 0.01721 -0.0776 0.9342 0.0536
-3.250 0.0307 0.02029 0.01596 -0.0773 0.9194 0.0550
-3.000 0.0599 0.01699 0.01209 -0.0767 0.9048 0.0491
-2.750 0.0866 0.01512 0.00989 -0.0763 0.8891 0.0485
-2.500 0.1134 0.01377 0.00827 -0.0757 0.8733 0.0485
-2.250 0.1403 0.01279 0.00707 -0.0752 0.8576 0.0488
-2.000 0.1675 0.01214 0.00622 -0.0747 0.8422 0.0496
-1.750 0.1948 0.01202 0.00597 -0.0742 0.8267 0.0507
-1.500 0.2221 0.01096 0.00473 -0.0739 0.8117 0.0519
-1.250 0.2493 0.01022 0.00390 -0.0736 0.7966 0.0532
-1.000 0.2767 0.00986 0.00348 -0.0733 0.7804 0.0547
-0.750 0.3043 0.00962 0.00318 -0.0730 0.7629 0.0565
-0.500 0.3318 0.00942 0.00291 -0.0727 0.7442 0.0586
-0.250 0.3595 0.00928 0.00271 -0.0725 0.7217 0.0612
0.000 0.3870 0.00919 0.00251 -0.0722 0.6958 0.0629
0.250 0.4143 0.00895 0.00214 -0.0719 0.6639 0.0661
0.500 0.4414 0.00896 0.00201 -0.0716 0.6261 0.0699
0.750 0.4685 0.00905 0.00194 -0.0714 0.5874 0.0743
1.000 0.4958 0.00911 0.00187 -0.0712 0.5539 0.0806
1.250 0.5232 0.00923 0.00187 -0.0710 0.5231 0.0895
1.500 0.5508 0.00924 0.00184 -0.0709 0.4971 0.1118
1.750 0.5730 0.00725 0.00196 -0.0702 0.4782 1.0000
2.000 0.6006 0.00746 0.00200 -0.0700 0.4589 1.0000
2.250 0.6283 0.00764 0.00207 -0.0699 0.4410 1.0000
2.500 0.6559 0.00783 0.00215 -0.0698 0.4244 1.0000
2.750 0.6835 0.00801 0.00224 -0.0697 0.4107 1.0000
3.000 0.7111 0.00819 0.00234 -0.0696 0.3980 1.0000
3.250 0.7388 0.00835 0.00245 -0.0695 0.3855 1.0000
3.500 0.7664 0.00852 0.00257 -0.0694 0.3733 1.0000
3.750 0.7940 0.00869 0.00270 -0.0693 0.3610 1.0000
4.000 0.8214 0.00887 0.00284 -0.0692 0.3483 1.0000
4.250 0.8487 0.00907 0.00299 -0.0690 0.3345 1.0000
4.500 0.8759 0.00928 0.00314 -0.0689 0.3189 1.0000
4.750 0.9029 0.00951 0.00332 -0.0688 0.3005 1.0000
5.000 0.9295 0.00980 0.00352 -0.0686 0.2762 1.0000
5.250 0.9548 0.01029 0.00377 -0.0683 0.2307 1.0000
5.500 0.9787 0.01104 0.00418 -0.0679 0.1726 1.0000
5.750 1.0035 0.01162 0.00461 -0.0676 0.1446 1.0000
6.000 1.0291 0.01205 0.00497 -0.0673 0.1323 1.0000
6.250 1.0545 0.01248 0.00535 -0.0670 0.1233 1.0000
6.500 1.0805 0.01280 0.00568 -0.0667 0.1164 1.0000
6.750 1.1059 0.01320 0.00606 -0.0664 0.1097 1.0000
7.000 1.1319 0.01348 0.00636 -0.0662 0.1035 1.0000
7.250 1.1573 0.01383 0.00669 -0.0659 0.0936 1.0000
7.500 1.1811 0.01443 0.00708 -0.0654 0.0615 1.0000
7.750 1.2001 0.01580 0.00825 -0.0643 0.0273 1.0000
8.000 1.2238 0.01639 0.00895 -0.0636 0.0250 1.0000
8.250 1.2459 0.01718 0.00982 -0.0628 0.0226 1.0000
8.500 1.2658 0.01826 0.01103 -0.0617 0.0206 1.0000
8.750 1.2879 0.01896 0.01181 -0.0609 0.0197 1.0000
9.000 1.3085 0.01979 0.01273 -0.0600 0.0186 1.0000
9.250 1.3279 0.02073 0.01375 -0.0589 0.0177 1.0000
9.500 1.3452 0.02183 0.01491 -0.0576 0.0169 1.0000
9.750 1.3551 0.02365 0.01685 -0.0554 0.0159 1.0000
10.000 1.3703 0.02481 0.01811 -0.0539 0.0154 1.0000
10.250 1.3862 0.02580 0.01920 -0.0524 0.0149 1.0000
10.500 1.3993 0.02701 0.02050 -0.0506 0.0144 1.0000
10.750 1.4102 0.02830 0.02189 -0.0487 0.0140 1.0000
11.000 1.4173 0.02964 0.02331 -0.0462 0.0136 1.0000
11.250 1.4226 0.03107 0.02484 -0.0436 0.0133 1.0000
11.500 1.4269 0.03267 0.02653 -0.0413 0.0130 1.0000
11.750 1.4301 0.03450 0.02844 -0.0393 0.0127 1.0000
12.000 1.4321 0.03659 0.03061 -0.0375 0.0125 1.0000
12.250 1.4326 0.03905 0.03313 -0.0359 0.0122 1.0000
12.500 1.4318 0.04223 0.03638 -0.0339 0.0119 1.0000
12.750 1.4323 0.04495 0.03925 -0.0327 0.0117 1.0000
13.000 1.4327 0.04738 0.04185 -0.0323 0.0115 1.0000
13.250 1.4324 0.05015 0.04478 -0.0321 0.0113 1.0000
13.500 1.4308 0.05325 0.04804 -0.0321 0.0111 1.0000
13.750 1.4277 0.05670 0.05166 -0.0323 0.0110 1.0000
14.000 1.4231 0.06049 0.05561 -0.0327 0.0108 1.0000
14.250 1.4169 0.06460 0.05988 -0.0335 0.0108 1.0000
14.500 1.4092 0.06907 0.06451 -0.0346 0.0107 1.0000
14.750 1.3999 0.07389 0.06950 -0.0361 0.0106 1.0000
15.000 1.3891 0.07910 0.07488 -0.0380 0.0106 1.0000
15.250 1.3772 0.08470 0.08064 -0.0403 0.0105 1.0000
15.500 1.3642 0.09065 0.08676 -0.0429 0.0105 1.0000
15.750 1.3501 0.09704 0.09330 -0.0459 0.0105 1.0000
16.000 1.3353 0.10383 0.10026 -0.0494 0.0105 1.0000
16.250 1.3194 0.11101 0.10760 -0.0532 0.0106 1.0000
16.500 1.3032 0.11856 0.11531 -0.0575 0.0106 1.0000
16.750 1.2863 0.12660 0.12351 -0.0622 0.0107 1.0000
17.000 1.2693 0.13500 0.13205 -0.0673 0.0107 1.0000
17.250 1.2516 0.14389 0.14109 -0.0728 0.0109 1.0000
17.500 1.2342 0.15319 0.15053 -0.0788 0.0110 1.0000
17.750 1.2162 0.16321 0.16068 -0.0853 0.0111 1.0000
18.000 1.1976 0.17397 0.17156 -0.0924 0.0113 1.0000
18.250 1.1785 0.18530 0.18298 -0.0996 0.0115 1.0000
18.500 1.1729 0.19193 0.18965 -0.1032 0.0119 1.0000
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