GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 500,000 Max Cl/Cd: 93.71 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe134-il-500000-n5.txt Download as CSV file: xf-goe134-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 134 (MVA H.12) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3814 0.08934 0.08714 -0.0260 1.0000 0.0089
-8.000 -0.3819 0.08654 0.08437 -0.0266 1.0000 0.0092
-7.750 -0.3898 0.08415 0.08202 -0.0258 1.0000 0.0093
-7.500 -0.3817 0.07990 0.07778 -0.0305 0.9968 0.0098
-7.250 -0.3641 0.07384 0.07170 -0.0391 0.9918 0.0101
-7.000 -0.3437 0.06667 0.06447 -0.0489 0.9866 0.0104
-6.750 -0.3233 0.05648 0.05412 -0.0602 0.9793 0.0110
-6.500 -0.2975 0.05314 0.05070 -0.0643 0.9749 0.0113
-6.250 -0.2738 0.05020 0.04768 -0.0671 0.9677 0.0116
-6.000 -0.2480 0.04646 0.04380 -0.0705 0.9611 0.0124
-5.750 -0.2227 0.03590 0.03271 -0.0754 0.9526 0.0141
-5.500 -0.1978 0.03441 0.03112 -0.0761 0.9439 0.0144
-5.250 -0.1725 0.03276 0.02934 -0.0768 0.9342 0.0148
-5.000 -0.1476 0.03043 0.02680 -0.0771 0.9221 0.0159
-4.750 -0.1210 0.02413 0.01982 -0.0772 0.9095 0.0179
-4.500 -0.0959 0.02340 0.01897 -0.0771 0.8923 0.0182
-4.250 -0.0707 0.02257 0.01798 -0.0769 0.8699 0.0189
-4.000 -0.0450 0.02101 0.01608 -0.0764 0.8395 0.0201
-3.750 -0.0181 0.01867 0.01309 -0.0756 0.8022 0.0214
-3.500 0.0078 0.01748 0.01149 -0.0753 0.7673 0.0224
-3.000 0.0616 0.01634 0.01000 -0.0753 0.7233 0.0236
-2.750 0.0895 0.01555 0.00897 -0.0753 0.7086 0.0240
-2.250 0.1460 0.01425 0.00730 -0.0753 0.6827 0.0252
-2.000 0.1744 0.01377 0.00666 -0.0753 0.6701 0.0260
-1.750 0.2027 0.01326 0.00601 -0.0753 0.6578 0.0263
-1.500 0.2310 0.01287 0.00550 -0.0754 0.6447 0.0266
-1.250 0.2593 0.01257 0.00509 -0.0754 0.6313 0.0269
-1.000 0.2875 0.01233 0.00474 -0.0755 0.6168 0.0271
-0.750 0.3155 0.01195 0.00429 -0.0755 0.6019 0.0274
-0.500 0.3433 0.01141 0.00371 -0.0756 0.5862 0.0280
-0.250 0.3712 0.01114 0.00339 -0.0757 0.5707 0.0287
0.000 0.3993 0.01096 0.00315 -0.0758 0.5555 0.0289
0.250 0.4275 0.01081 0.00293 -0.0759 0.5404 0.0291
0.500 0.4556 0.01070 0.00276 -0.0760 0.5257 0.0294
0.750 0.4838 0.01061 0.00263 -0.0762 0.5121 0.0299
1.000 0.5121 0.01056 0.00252 -0.0763 0.4990 0.0304
1.250 0.5404 0.01053 0.00245 -0.0765 0.4856 0.0311
1.500 0.5685 0.01053 0.00240 -0.0766 0.4715 0.0318
1.750 0.5966 0.01056 0.00237 -0.0767 0.4574 0.0325
2.000 0.6247 0.01061 0.00237 -0.0768 0.4444 0.0334
2.250 0.6527 0.01068 0.00238 -0.0769 0.4319 0.0347
2.500 0.6807 0.01075 0.00240 -0.0770 0.4195 0.0357
3.000 0.7364 0.01094 0.00251 -0.0772 0.3943 0.0398
3.250 0.7640 0.00991 0.00275 -0.0781 0.3822 0.6280
3.750 0.8120 0.00934 0.00293 -0.0763 0.3616 1.0000
4.000 0.8397 0.00950 0.00306 -0.0763 0.3518 1.0000
4.250 0.8671 0.00970 0.00320 -0.0764 0.3413 1.0000
4.500 0.8943 0.00992 0.00336 -0.0764 0.3306 1.0000
4.750 0.9216 0.01012 0.00354 -0.0765 0.3198 1.0000
5.000 0.9488 0.01033 0.00371 -0.0765 0.3094 1.0000
5.250 0.9757 0.01057 0.00391 -0.0765 0.2984 1.0000
5.500 1.0024 0.01082 0.00412 -0.0765 0.2869 1.0000
5.750 1.0292 0.01105 0.00433 -0.0765 0.2749 1.0000
6.000 1.0558 0.01130 0.00455 -0.0764 0.2640 1.0000
6.250 1.0823 0.01155 0.00479 -0.0764 0.2545 1.0000
6.500 1.1084 0.01185 0.00505 -0.0763 0.2422 1.0000
6.750 1.1341 0.01216 0.00532 -0.0761 0.2272 1.0000
7.000 1.1597 0.01250 0.00561 -0.0760 0.2118 1.0000
7.250 1.1848 0.01287 0.00595 -0.0758 0.1937 1.0000
7.500 1.2087 0.01338 0.00634 -0.0754 0.1677 1.0000
7.750 1.2295 0.01423 0.00694 -0.0746 0.1255 1.0000
8.000 1.2507 0.01500 0.00757 -0.0739 0.0994 1.0000
8.250 1.2723 0.01569 0.00816 -0.0732 0.0789 1.0000
8.500 1.2931 0.01643 0.00879 -0.0724 0.0596 1.0000
8.750 1.3130 0.01723 0.00949 -0.0714 0.0417 1.0000
9.000 1.3286 0.01843 0.01052 -0.0698 0.0165 1.0000
9.250 1.3493 0.01904 0.01121 -0.0689 0.0141 1.0000
9.500 1.3686 0.01976 0.01200 -0.0678 0.0124 1.0000
9.750 1.3874 0.02047 0.01279 -0.0666 0.0111 1.0000
10.000 1.4063 0.02111 0.01352 -0.0654 0.0102 1.0000
10.250 1.4238 0.02182 0.01433 -0.0641 0.0095 1.0000
10.500 1.4391 0.02263 0.01522 -0.0624 0.0089 1.0000
10.750 1.4511 0.02361 0.01629 -0.0602 0.0084 1.0000
11.000 1.4601 0.02462 0.01740 -0.0576 0.0080 1.0000
11.250 1.4688 0.02554 0.01843 -0.0549 0.0077 1.0000
11.500 1.4770 0.02658 0.01956 -0.0524 0.0074 1.0000
11.750 1.4841 0.02775 0.02085 -0.0500 0.0071 1.0000
12.000 1.4908 0.02904 0.02223 -0.0478 0.0067 1.0000
12.250 1.4965 0.03047 0.02376 -0.0458 0.0064 1.0000
12.500 1.5008 0.03213 0.02551 -0.0439 0.0062 1.0000
12.750 1.5023 0.03414 0.02763 -0.0422 0.0060 1.0000
13.000 1.5006 0.03665 0.03026 -0.0408 0.0058 1.0000
13.250 1.4944 0.03988 0.03363 -0.0398 0.0057 1.0000
13.500 1.4941 0.04274 0.03662 -0.0394 0.0056 1.0000
13.750 1.4924 0.04594 0.03996 -0.0394 0.0055 1.0000
14.000 1.4886 0.04951 0.04368 -0.0396 0.0054 1.0000
14.250 1.4830 0.05346 0.04776 -0.0401 0.0053 1.0000
14.500 1.4764 0.05765 0.05208 -0.0408 0.0053 1.0000
14.750 1.4681 0.06216 0.05674 -0.0417 0.0052 1.0000
15.000 1.4588 0.06694 0.06165 -0.0429 0.0051 1.0000
15.250 1.4485 0.07199 0.06683 -0.0442 0.0050 1.0000
15.500 1.4377 0.07719 0.07216 -0.0456 0.0050 1.0000
15.750 1.4266 0.08257 0.07767 -0.0473 0.0049 1.0000
16.000 1.4153 0.08810 0.08332 -0.0490 0.0049 1.0000
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Polar data table (+)
Polar graphs
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