GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 100,000 Max Cl/Cd: 63.49 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610bm-il-100000-n5.txt Download as CSV file: xf-goe610bm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610-B MOD. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2952 0.10517 0.10078 -0.0314 1.0000 0.0338
-7.250 -0.2986 0.10354 0.09923 -0.0314 1.0000 0.0339
-7.000 -0.3025 0.10186 0.09764 -0.0310 1.0000 0.0340
-6.750 -0.2928 0.09881 0.09462 -0.0342 0.9969 0.0341
-6.500 -0.2635 0.09384 0.08960 -0.0425 0.9896 0.0341
-6.250 -0.2332 0.08875 0.08447 -0.0502 0.9825 0.0342
-6.000 -0.2012 0.08356 0.07919 -0.0579 0.9758 0.0343
-5.750 -0.1896 0.07693 0.07262 -0.0580 0.9707 0.0354
-5.500 -0.1678 0.07272 0.06839 -0.0601 0.9639 0.0369
-5.250 -0.1395 0.06894 0.06457 -0.0648 0.9565 0.0410
-5.000 -0.0701 0.06414 0.05944 -0.0853 0.9478 0.0478
-4.750 -0.0323 0.05945 0.05455 -0.0923 0.9394 0.0480
-4.500 -0.0157 0.05391 0.04908 -0.0937 0.9319 0.0495
-4.250 0.0168 0.04996 0.04498 -0.0974 0.9250 0.0459
-4.000 0.0579 0.04623 0.04098 -0.1050 0.9160 0.0642
-3.750 0.0929 0.04083 0.03538 -0.1083 0.9097 0.0440
-3.500 0.1310 0.03648 0.03069 -0.1127 0.9005 0.0424
-3.250 0.1747 0.03236 0.02598 -0.1173 0.8933 0.0461
-3.000 0.2108 0.02905 0.02217 -0.1198 0.8844 0.0462
-2.750 0.2462 0.02638 0.01886 -0.1217 0.8752 0.0491
-2.500 0.2773 0.02445 0.01668 -0.1228 0.8667 0.0515
-2.250 0.3084 0.02275 0.01454 -0.1234 0.8559 0.0518
-2.000 0.3386 0.02143 0.01287 -0.1237 0.8452 0.0526
-1.750 0.3678 0.02053 0.01170 -0.1238 0.8347 0.0557
-1.500 0.3970 0.01971 0.01060 -0.1236 0.8241 0.0586
-1.250 0.4255 0.01888 0.00955 -0.1234 0.8118 0.0584
-1.000 0.4536 0.01819 0.00867 -0.1231 0.7997 0.0584
-0.750 0.4816 0.01759 0.00794 -0.1228 0.7876 0.0587
-0.500 0.5092 0.01709 0.00733 -0.1224 0.7754 0.0593
-0.250 0.5367 0.01669 0.00681 -0.1220 0.7630 0.0602
0.000 0.5643 0.01639 0.00638 -0.1216 0.7504 0.0616
0.250 0.5919 0.01614 0.00602 -0.1213 0.7369 0.0638
0.500 0.6196 0.01595 0.00572 -0.1210 0.7231 0.0687
0.750 0.6474 0.01585 0.00549 -0.1208 0.7092 0.0775
1.000 0.6757 0.01531 0.00547 -0.1210 0.6952 0.2505
1.500 0.7239 0.01401 0.00534 -0.1190 0.6672 1.0000
1.750 0.7512 0.01419 0.00535 -0.1188 0.6531 1.0000
2.000 0.7784 0.01438 0.00539 -0.1186 0.6394 1.0000
2.250 0.8056 0.01457 0.00547 -0.1184 0.6264 1.0000
2.500 0.8328 0.01478 0.00556 -0.1182 0.6143 1.0000
2.750 0.8598 0.01500 0.00567 -0.1179 0.6030 1.0000
3.000 0.8869 0.01523 0.00586 -0.1178 0.5916 1.0000
3.250 0.9139 0.01549 0.00605 -0.1176 0.5815 1.0000
3.500 0.9409 0.01575 0.00623 -0.1174 0.5726 1.0000
3.750 0.9678 0.01604 0.00653 -0.1173 0.5631 1.0000
4.000 0.9947 0.01635 0.00681 -0.1172 0.5548 1.0000
4.250 1.0215 0.01666 0.00713 -0.1170 0.5466 1.0000
4.500 1.0481 0.01700 0.00748 -0.1169 0.5381 1.0000
4.750 1.0743 0.01733 0.00781 -0.1166 0.5280 1.0000
5.000 1.1000 0.01766 0.00817 -0.1162 0.5154 1.0000
5.250 1.1253 0.01800 0.00854 -0.1158 0.5018 1.0000
5.500 1.1505 0.01833 0.00897 -0.1154 0.4888 1.0000
5.750 1.1756 0.01867 0.00938 -0.1149 0.4762 1.0000
6.000 1.1999 0.01898 0.00977 -0.1143 0.4600 1.0000
6.250 1.2216 0.01924 0.01002 -0.1132 0.4299 1.0000
6.500 1.2428 0.01959 0.01037 -0.1122 0.3965 1.0000
6.750 1.2642 0.02002 0.01080 -0.1112 0.3611 1.0000
7.000 1.2827 0.02075 0.01130 -0.1099 0.3024 1.0000
7.250 1.2975 0.02196 0.01211 -0.1082 0.2299 1.0000
7.500 1.3076 0.02382 0.01346 -0.1061 0.1612 1.0000
7.750 1.3189 0.02552 0.01486 -0.1042 0.1137 1.0000
8.000 1.3334 0.02677 0.01608 -0.1025 0.0811 1.0000
8.250 1.3334 0.02927 0.01808 -0.0991 0.0259 1.0000
8.500 1.3429 0.03076 0.01965 -0.0967 0.0219 1.0000
8.750 1.3529 0.03210 0.02120 -0.0943 0.0204 1.0000
9.000 1.3606 0.03349 0.02281 -0.0916 0.0195 1.0000
9.250 1.3650 0.03500 0.02453 -0.0886 0.0188 1.0000
9.500 1.3686 0.03673 0.02648 -0.0858 0.0183 1.0000
9.750 1.3704 0.03872 0.02867 -0.0832 0.0176 1.0000
10.000 1.3700 0.04100 0.03117 -0.0808 0.0168 1.0000
10.250 1.3677 0.04360 0.03397 -0.0786 0.0160 1.0000
10.500 1.3635 0.04651 0.03708 -0.0767 0.0153 1.0000
10.750 1.3584 0.04968 0.04044 -0.0751 0.0149 1.0000
11.000 1.3538 0.05294 0.04388 -0.0738 0.0146 1.0000
11.250 1.3496 0.05629 0.04746 -0.0727 0.0144 1.0000
11.500 1.3461 0.05964 0.05095 -0.0715 0.0142 1.0000
11.750 1.3445 0.06284 0.05427 -0.0703 0.0140 1.0000
12.000 1.3461 0.06576 0.05731 -0.0688 0.0139 1.0000
12.250 1.3515 0.06845 0.06011 -0.0670 0.0137 1.0000
12.500 1.3573 0.07119 0.06297 -0.0656 0.0136 1.0000
12.750 1.3609 0.07419 0.06617 -0.0648 0.0135 1.0000
13.000 1.3613 0.07752 0.06973 -0.0643 0.0133 1.0000
13.250 1.3597 0.08114 0.07358 -0.0642 0.0131 1.0000
13.500 1.3562 0.08505 0.07774 -0.0644 0.0128 1.0000
13.750 1.3512 0.08924 0.08217 -0.0649 0.0126 1.0000
14.000 1.3451 0.09374 0.08690 -0.0657 0.0124 1.0000
14.250 1.3378 0.09859 0.09198 -0.0669 0.0122 1.0000
14.500 1.3293 0.10381 0.09745 -0.0686 0.0121 1.0000
14.750 1.3198 0.10938 0.10325 -0.0707 0.0120 1.0000
15.000 1.3094 0.11532 0.10941 -0.0733 0.0120 1.0000
15.250 1.2983 0.12166 0.11598 -0.0764 0.0120 1.0000
15.500 1.2866 0.12842 0.12295 -0.0800 0.0120 1.0000
15.750 1.2745 0.13562 0.13036 -0.0842 0.0121 1.0000
16.000 1.2620 0.14330 0.13824 -0.0890 0.0121 1.0000
16.250 1.2495 0.15145 0.14657 -0.0943 0.0122 1.0000
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Polar data table (+)
Polar graphs
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