GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 563 AIRFOIL (goe563-il) Reynolds number: 200,000 Max Cl/Cd: 64.23 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe563-il-200000-n5.txt Download as CSV file: xf-goe563-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 563 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4914 0.11324 0.10931 -0.0242 1.0000 0.0209
-11.250 -0.4962 0.10754 0.10363 -0.0266 1.0000 0.0213
-11.000 -0.5039 0.10123 0.09736 -0.0292 1.0000 0.0216
-10.500 -0.5096 0.09254 0.08874 -0.0326 1.0000 0.0221
-10.250 -0.5071 0.08974 0.08596 -0.0335 1.0000 0.0226
-10.000 -0.5045 0.08701 0.08326 -0.0344 1.0000 0.0233
-9.750 -0.5095 0.08267 0.07896 -0.0363 1.0000 0.0236
-9.500 -0.5143 0.07866 0.07500 -0.0381 1.0000 0.0245
-9.250 -0.5335 0.07228 0.06871 -0.0413 1.0000 0.0244
-9.000 -0.5679 0.06449 0.06103 -0.0460 1.0000 0.0242
-8.750 -0.6542 0.04416 0.04023 -0.0515 1.0000 0.0236
-8.500 -0.6584 0.04087 0.03671 -0.0495 1.0000 0.0244
-8.250 -0.6638 0.03679 0.03224 -0.0472 1.0000 0.0256
-8.000 -0.6664 0.03255 0.02744 -0.0446 1.0000 0.0269
-7.750 -0.6468 0.02892 0.02305 -0.0453 0.9969 0.0285
-7.500 -0.6205 0.02697 0.02094 -0.0466 0.9936 0.0301
-7.250 -0.5921 0.02610 0.01996 -0.0476 0.9902 0.0316
-7.000 -0.5631 0.02469 0.01824 -0.0487 0.9870 0.0333
-6.750 -0.5336 0.02334 0.01658 -0.0497 0.9840 0.0353
-6.500 -0.5056 0.02225 0.01516 -0.0501 0.9800 0.0369
-6.250 -0.4764 0.02071 0.01335 -0.0509 0.9769 0.0380
-6.000 -0.4452 0.01964 0.01220 -0.0521 0.9746 0.0399
-5.750 -0.4178 0.01893 0.01138 -0.0523 0.9701 0.0415
-5.500 -0.3876 0.01810 0.01041 -0.0530 0.9665 0.0428
-5.250 -0.3554 0.01731 0.00950 -0.0541 0.9639 0.0441
-5.000 -0.3228 0.01663 0.00871 -0.0552 0.9614 0.0455
-4.750 -0.2958 0.01612 0.00808 -0.0551 0.9561 0.0471
-4.500 -0.2644 0.01548 0.00737 -0.0559 0.9526 0.0485
-4.250 -0.2315 0.01478 0.00667 -0.0571 0.9500 0.0505
-4.000 -0.1996 0.01431 0.00616 -0.0580 0.9466 0.0527
-3.750 -0.1723 0.01393 0.00575 -0.0579 0.9407 0.0551
-3.500 -0.1401 0.01355 0.00532 -0.0588 0.9369 0.0585
-3.250 -0.1064 0.01314 0.00492 -0.0601 0.9339 0.0642
-3.000 -0.0802 0.01286 0.00469 -0.0597 0.9270 0.0741
-2.750 -0.0491 0.01255 0.00446 -0.0603 0.9221 0.0940
-2.500 -0.0156 0.01227 0.00418 -0.0614 0.9186 0.1127
-2.250 0.0093 0.01205 0.00401 -0.0608 0.9105 0.1274
-2.000 0.0403 0.01178 0.00380 -0.0614 0.9056 0.1471
-1.750 0.0676 0.01154 0.00366 -0.0613 0.8990 0.1760
-1.500 0.0946 0.01107 0.00350 -0.0612 0.8924 0.2470
-1.250 0.1179 0.01026 0.00344 -0.0606 0.8859 0.4463
-1.000 0.1405 0.00976 0.00339 -0.0594 0.8781 0.5674
-0.750 0.1637 0.00929 0.00336 -0.0579 0.8703 0.6868
-0.500 0.1921 0.00890 0.00334 -0.0572 0.8614 0.8092
-0.250 0.2416 0.00873 0.00329 -0.0610 0.8504 0.9054
0.000 0.2938 0.00864 0.00316 -0.0656 0.8375 0.9566
0.250 0.3407 0.00859 0.00304 -0.0693 0.8245 0.9833
0.500 0.3862 0.00856 0.00294 -0.0730 0.8125 0.9997
0.750 0.4109 0.00857 0.00288 -0.0721 0.7986 1.0000
1.000 0.4350 0.00859 0.00283 -0.0712 0.7842 1.0000
1.250 0.4591 0.00863 0.00281 -0.0702 0.7691 1.0000
1.500 0.4831 0.00869 0.00281 -0.0692 0.7524 1.0000
1.750 0.5069 0.00876 0.00280 -0.0681 0.7329 1.0000
2.000 0.5303 0.00886 0.00281 -0.0670 0.7090 1.0000
2.250 0.5530 0.00899 0.00282 -0.0656 0.6800 1.0000
2.500 0.5754 0.00916 0.00286 -0.0643 0.6480 1.0000
2.750 0.5969 0.00937 0.00292 -0.0628 0.6102 1.0000
3.000 0.6179 0.00963 0.00301 -0.0612 0.5702 1.0000
3.250 0.6384 0.00994 0.00314 -0.0596 0.5312 1.0000
3.500 0.6588 0.01028 0.00330 -0.0580 0.4901 1.0000
3.750 0.6785 0.01067 0.00351 -0.0564 0.4458 1.0000
4.000 0.6979 0.01111 0.00375 -0.0547 0.4004 1.0000
4.250 0.7173 0.01159 0.00402 -0.0531 0.3581 1.0000
4.500 0.7373 0.01205 0.00433 -0.0517 0.3242 1.0000
4.750 0.7580 0.01250 0.00464 -0.0504 0.2942 1.0000
5.000 0.7792 0.01291 0.00496 -0.0492 0.2662 1.0000
5.250 0.8008 0.01332 0.00529 -0.0481 0.2407 1.0000
5.500 0.8222 0.01375 0.00565 -0.0469 0.2154 1.0000
5.750 0.8432 0.01422 0.00601 -0.0458 0.1874 1.0000
6.000 0.8640 0.01473 0.00641 -0.0446 0.1602 1.0000
6.250 0.8847 0.01525 0.00684 -0.0435 0.1378 1.0000
6.500 0.9055 0.01577 0.00733 -0.0423 0.1214 1.0000
6.750 0.9262 0.01631 0.00784 -0.0412 0.1061 1.0000
7.000 0.9467 0.01689 0.00838 -0.0400 0.0881 1.0000
7.250 0.9664 0.01754 0.00894 -0.0388 0.0660 1.0000
7.500 0.9852 0.01827 0.00959 -0.0374 0.0524 1.0000
7.750 1.0040 0.01900 0.01033 -0.0360 0.0453 1.0000
8.000 1.0223 0.01975 0.01112 -0.0345 0.0407 1.0000
8.250 1.0405 0.02048 0.01193 -0.0330 0.0369 1.0000
8.500 1.0555 0.02149 0.01297 -0.0311 0.0336 1.0000
8.750 1.0729 0.02225 0.01385 -0.0295 0.0312 1.0000
9.000 1.0894 0.02307 0.01476 -0.0279 0.0285 1.0000
9.250 1.1033 0.02406 0.01585 -0.0260 0.0266 1.0000
9.500 1.1137 0.02533 0.01718 -0.0236 0.0249 1.0000
9.750 1.1276 0.02621 0.01821 -0.0215 0.0234 1.0000
10.000 1.1399 0.02717 0.01928 -0.0194 0.0219 1.0000
10.250 1.1516 0.02810 0.02030 -0.0173 0.0203 1.0000
10.500 1.1605 0.02930 0.02157 -0.0149 0.0195 1.0000
10.750 1.1657 0.03094 0.02325 -0.0124 0.0186 1.0000
11.000 1.1756 0.03223 0.02472 -0.0103 0.0179 1.0000
11.250 1.1841 0.03365 0.02635 -0.0083 0.0171 1.0000
11.500 1.1915 0.03514 0.02801 -0.0064 0.0163 1.0000
11.750 1.1978 0.03665 0.02965 -0.0045 0.0156 1.0000
12.000 1.2030 0.03817 0.03129 -0.0028 0.0149 1.0000
12.250 1.2066 0.03996 0.03321 -0.0012 0.0145 1.0000
12.500 1.2085 0.04196 0.03532 0.0002 0.0141 1.0000
12.750 1.2073 0.04442 0.03791 0.0015 0.0137 1.0000
13.000 1.2035 0.04740 0.04104 0.0026 0.0134 1.0000
13.250 1.2005 0.05033 0.04420 0.0033 0.0133 1.0000
13.500 1.1942 0.05378 0.04789 0.0036 0.0131 1.0000
13.750 1.1865 0.05755 0.05189 0.0034 0.0129 1.0000
14.000 1.1759 0.06195 0.05651 0.0026 0.0128 1.0000
14.250 1.1638 0.06683 0.06162 0.0011 0.0127 1.0000
14.500 1.1487 0.07255 0.06756 -0.0013 0.0126 1.0000
14.750 1.1329 0.07879 0.07401 -0.0044 0.0126 1.0000
15.000 1.1152 0.08592 0.08135 -0.0084 0.0126 1.0000
15.250 1.0947 0.09421 0.08984 -0.0135 0.0125 1.0000
15.500 1.0718 0.10362 0.09944 -0.0193 0.0126 1.0000
15.750 1.0490 0.11357 0.10956 -0.0255 0.0128 1.0000
16.000 1.0212 0.12529 0.12144 -0.0327 0.0130 1.0000
16.250 0.9893 0.13898 0.13526 -0.0409 0.0132 1.0000
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