GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 177 AIRFOIL (goe177-il) Reynolds number: 100,000 Max Cl/Cd: 57.83 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe177-il-100000-n5.txt Download as CSV file: xf-goe177-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 177 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2980 0.09486 0.09049 -0.0228 1.0000 0.0395
-7.000 -0.3001 0.09330 0.08903 -0.0251 1.0000 0.0407
-6.750 -0.2976 0.09132 0.08715 -0.0291 1.0000 0.0412
-6.500 -0.2915 0.08877 0.08465 -0.0326 1.0000 0.0414
-6.250 -0.2838 0.08586 0.08179 -0.0352 1.0000 0.0415
-6.000 -0.2790 0.08214 0.07815 -0.0357 1.0000 0.0417
-5.750 -0.2765 0.07853 0.07460 -0.0341 1.0000 0.0421
-5.500 -0.2614 0.07475 0.07083 -0.0374 0.9978 0.0421
-5.250 -0.2398 0.06922 0.06523 -0.0382 0.9913 0.0294
-5.000 -0.2028 0.06363 0.05957 -0.0466 0.9822 0.0263
-4.750 -0.1587 0.05700 0.05280 -0.0572 0.9725 0.0238
-4.500 -0.1046 0.04837 0.04390 -0.0699 0.9634 0.0215
-4.250 -0.0581 0.04197 0.03723 -0.0780 0.9544 0.0213
-4.000 -0.0228 0.03896 0.03404 -0.0823 0.9417 0.0237
-3.750 0.0192 0.03367 0.02835 -0.0876 0.9285 0.0250
-3.500 0.0618 0.02733 0.02128 -0.0923 0.9146 0.0252
-3.250 0.1013 0.02261 0.01566 -0.0949 0.8992 0.0266
-3.000 0.1379 0.01981 0.01205 -0.0962 0.8815 0.0309
-2.750 0.1715 0.01829 0.01025 -0.0970 0.8608 0.0360
-2.500 0.2048 0.01732 0.00903 -0.0975 0.8394 0.0461
-2.250 0.2365 0.01670 0.00808 -0.0975 0.8171 0.0656
-2.000 0.2660 0.01638 0.00753 -0.0975 0.7947 0.0898
-1.750 0.2947 0.01601 0.00689 -0.0972 0.7730 0.1081
-1.500 0.3225 0.01567 0.00638 -0.0969 0.7522 0.1211
-1.250 0.3499 0.01541 0.00595 -0.0966 0.7323 0.1330
-1.000 0.3771 0.01516 0.00551 -0.0961 0.7136 0.1408
-0.750 0.4039 0.01497 0.00518 -0.0956 0.6953 0.1493
-0.500 0.4306 0.01482 0.00492 -0.0951 0.6777 0.1624
-0.250 0.4577 0.01470 0.00470 -0.0948 0.6606 0.1802
0.000 0.4847 0.01454 0.00457 -0.0945 0.6442 0.2208
0.250 0.5113 0.01432 0.00452 -0.0942 0.6283 0.3254
0.500 0.5301 0.01315 0.00447 -0.0921 0.6139 0.7400
1.000 0.5884 0.01326 0.00428 -0.0921 0.5835 1.0000
1.250 0.6150 0.01346 0.00430 -0.0917 0.5693 1.0000
1.500 0.6417 0.01368 0.00435 -0.0914 0.5554 1.0000
1.750 0.6682 0.01390 0.00443 -0.0911 0.5418 1.0000
2.000 0.6947 0.01413 0.00454 -0.0908 0.5288 1.0000
2.250 0.7212 0.01437 0.00467 -0.0905 0.5165 1.0000
2.500 0.7474 0.01462 0.00483 -0.0902 0.5028 1.0000
2.750 0.7733 0.01487 0.00497 -0.0898 0.4873 1.0000
3.000 0.7989 0.01512 0.00512 -0.0894 0.4710 1.0000
3.250 0.8246 0.01538 0.00530 -0.0890 0.4556 1.0000
3.500 0.8504 0.01564 0.00555 -0.0887 0.4428 1.0000
3.750 0.8763 0.01592 0.00580 -0.0883 0.4320 1.0000
4.000 0.9019 0.01621 0.00605 -0.0880 0.4208 1.0000
4.250 0.9274 0.01650 0.00637 -0.0876 0.4088 1.0000
4.500 0.9529 0.01679 0.00668 -0.0873 0.3967 1.0000
4.750 0.9783 0.01709 0.00702 -0.0869 0.3853 1.0000
5.000 1.0035 0.01740 0.00737 -0.0865 0.3750 1.0000
5.250 1.0265 0.01775 0.00766 -0.0859 0.3479 1.0000
5.500 1.0494 0.01817 0.00798 -0.0852 0.3195 1.0000
5.750 1.0723 0.01865 0.00838 -0.0846 0.2886 1.0000
6.000 1.0944 0.01927 0.00884 -0.0839 0.2446 1.0000
6.250 1.1068 0.02122 0.00997 -0.0824 0.1218 1.0000
6.500 1.1219 0.02295 0.01138 -0.0811 0.0574 1.0000
6.750 1.1433 0.02376 0.01231 -0.0802 0.0482 1.0000
7.000 1.1628 0.02478 0.01335 -0.0791 0.0219 1.0000
7.250 1.1815 0.02584 0.01457 -0.0778 0.0188 1.0000
7.500 1.1999 0.02689 0.01584 -0.0765 0.0176 1.0000
7.750 1.2166 0.02806 0.01726 -0.0750 0.0168 1.0000
8.000 1.2304 0.02945 0.01892 -0.0733 0.0159 1.0000
8.250 1.2401 0.03113 0.02096 -0.0712 0.0147 1.0000
8.500 1.2452 0.03305 0.02316 -0.0687 0.0138 1.0000
8.750 1.2466 0.03502 0.02538 -0.0659 0.0134 1.0000
9.000 1.2440 0.03710 0.02768 -0.0629 0.0132 1.0000
9.250 1.2401 0.03947 0.03024 -0.0604 0.0131 1.0000
9.500 1.2356 0.04214 0.03308 -0.0584 0.0130 1.0000
9.750 1.2322 0.04497 0.03605 -0.0569 0.0129 1.0000
10.000 1.2306 0.04781 0.03900 -0.0556 0.0128 1.0000
10.250 1.2327 0.05042 0.04170 -0.0540 0.0127 1.0000
10.500 1.2393 0.05277 0.04411 -0.0521 0.0127 1.0000
10.750 1.2503 0.05496 0.04635 -0.0501 0.0126 1.0000
11.000 1.2595 0.05732 0.04887 -0.0488 0.0125 1.0000
11.250 1.2658 0.05988 0.05165 -0.0479 0.0122 1.0000
11.500 1.2701 0.06271 0.05469 -0.0472 0.0119 1.0000
11.750 1.2729 0.06578 0.05799 -0.0466 0.0116 1.0000
12.000 1.2739 0.06915 0.06159 -0.0462 0.0113 1.0000
12.250 1.2726 0.07286 0.06554 -0.0460 0.0112 1.0000
12.500 1.2694 0.07692 0.06984 -0.0461 0.0112 1.0000
12.750 1.2637 0.08136 0.07453 -0.0466 0.0112 1.0000
13.000 1.2554 0.08617 0.07958 -0.0477 0.0113 1.0000
13.250 1.2452 0.09134 0.08499 -0.0492 0.0114 1.0000
13.500 1.2337 0.09682 0.09069 -0.0511 0.0114 1.0000
13.750 1.2210 0.10263 0.09672 -0.0536 0.0115 1.0000
14.000 1.2080 0.10877 0.10307 -0.0565 0.0116 1.0000
14.250 1.1946 0.11528 0.10978 -0.0599 0.0117 1.0000
14.500 1.1812 0.12212 0.11681 -0.0637 0.0117 1.0000
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Polar data table (+)
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