WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Reynolds number: 200,000 Max Cl/Cd: 71.48 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66a175-il-200000-n5.txt Download as CSV file: xf-fx66a175-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17A-175 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2238 0.09268 0.08792 -0.0794 0.6516 0.0124
-11.500 -0.2311 0.08630 0.08154 -0.0824 0.6467 0.0121
-11.250 -0.2568 0.07452 0.06975 -0.0886 0.6456 0.0117
-11.000 -0.2843 0.06557 0.06068 -0.0946 0.6429 0.0115
-10.750 -0.3075 0.05908 0.05405 -0.0989 0.6392 0.0114
-10.500 -0.3256 0.05406 0.04888 -0.1020 0.6345 0.0111
-10.250 -0.3442 0.04944 0.04407 -0.1044 0.6300 0.0111
-10.000 -0.3604 0.04546 0.03987 -0.1061 0.6257 0.0111
-9.750 -0.3729 0.04224 0.03646 -0.1068 0.6208 0.0110
-9.500 -0.3863 0.03965 0.03362 -0.1056 0.6162 0.0111
-9.250 -0.3892 0.03707 0.03072 -0.1046 0.6119 0.0111
-9.000 -0.3862 0.03452 0.02785 -0.1036 0.6069 0.0113
-8.750 -0.3780 0.03223 0.02522 -0.1026 0.6019 0.0115
-8.500 -0.3657 0.03018 0.02281 -0.1016 0.5974 0.0118
-8.250 -0.3496 0.02840 0.02076 -0.1007 0.5921 0.0120
-8.000 -0.3316 0.02685 0.01893 -0.0999 0.5871 0.0125
-7.750 -0.3120 0.02559 0.01741 -0.0991 0.5832 0.0128
-7.500 -0.2926 0.02421 0.01590 -0.0983 0.5786 0.0134
-7.250 -0.2725 0.02328 0.01490 -0.0978 0.5742 0.0144
-7.000 -0.2509 0.02260 0.01411 -0.0973 0.5705 0.0156
-6.750 -0.2295 0.02174 0.01312 -0.0966 0.5670 0.0165
-6.500 -0.2081 0.02087 0.01216 -0.0959 0.5632 0.0173
-6.250 -0.1863 0.02011 0.01128 -0.0952 0.5597 0.0181
-6.000 -0.1652 0.01929 0.01035 -0.0946 0.5566 0.0190
-5.750 -0.1433 0.01856 0.00951 -0.0941 0.5538 0.0207
-5.500 -0.1191 0.01805 0.00893 -0.0939 0.5503 0.0236
-5.250 -0.0947 0.01754 0.00830 -0.0936 0.5469 0.0269
-5.000 -0.0707 0.01696 0.00763 -0.0933 0.5439 0.0322
-4.750 -0.0461 0.01645 0.00706 -0.0931 0.5413 0.0450
-4.500 -0.0225 0.01574 0.00653 -0.0929 0.5387 0.0915
-4.250 -0.0003 0.01479 0.00600 -0.0929 0.5356 0.1970
-4.000 0.0200 0.01394 0.00599 -0.0924 0.5326 0.3964
-3.750 0.0476 0.01420 0.00617 -0.0922 0.5296 0.4477
-3.500 0.0753 0.01447 0.00630 -0.0920 0.5270 0.4689
-3.250 0.1028 0.01476 0.00645 -0.0917 0.5244 0.4864
-3.000 0.1303 0.01496 0.00660 -0.0915 0.5215 0.4980
-2.750 0.1579 0.01509 0.00664 -0.0914 0.5188 0.5070
-2.500 0.1857 0.01514 0.00660 -0.0914 0.5163 0.5121
-2.250 0.2138 0.01516 0.00646 -0.0915 0.5141 0.5165
-2.000 0.2418 0.01518 0.00633 -0.0916 0.5121 0.5197
-1.750 0.2697 0.01520 0.00629 -0.0917 0.5099 0.5223
-1.500 0.2976 0.01520 0.00625 -0.0918 0.5074 0.5244
-1.250 0.3255 0.01521 0.00618 -0.0920 0.5050 0.5266
-1.000 0.3534 0.01524 0.00612 -0.0921 0.5027 0.5291
-0.750 0.3815 0.01527 0.00605 -0.0923 0.5006 0.5314
-0.500 0.4096 0.01530 0.00598 -0.0925 0.4988 0.5333
-0.250 0.4376 0.01535 0.00596 -0.0927 0.4971 0.5348
0.000 0.4652 0.01539 0.00600 -0.0928 0.4949 0.5365
0.250 0.4926 0.01544 0.00604 -0.0929 0.4924 0.5383
0.500 0.5202 0.01549 0.00609 -0.0930 0.4900 0.5403
0.750 0.5478 0.01556 0.00612 -0.0931 0.4879 0.5426
1.000 0.5755 0.01564 0.00616 -0.0933 0.4860 0.5451
1.250 0.6034 0.01573 0.00619 -0.0935 0.4844 0.5474
1.500 0.6313 0.01582 0.00625 -0.0936 0.4829 0.5491
1.750 0.6585 0.01591 0.00638 -0.0937 0.4810 0.5509
2.000 0.6852 0.01601 0.00652 -0.0937 0.4786 0.5529
2.250 0.7121 0.01610 0.00665 -0.0937 0.4762 0.5552
2.500 0.7391 0.01620 0.00676 -0.0938 0.4739 0.5579
2.750 0.7664 0.01631 0.00688 -0.0939 0.4720 0.5607
3.000 0.7937 0.01642 0.00699 -0.0940 0.4704 0.5632
3.250 0.8211 0.01654 0.00713 -0.0941 0.4690 0.5656
3.500 0.8482 0.01669 0.00733 -0.0942 0.4675 0.5684
3.750 0.8741 0.01687 0.00760 -0.0941 0.4656 0.5713
4.000 0.9001 0.01704 0.00785 -0.0940 0.4636 0.5743
4.250 0.9263 0.01721 0.00809 -0.0940 0.4616 0.5772
4.500 0.9525 0.01735 0.00832 -0.0940 0.4597 0.5800
4.750 0.9789 0.01751 0.00854 -0.0939 0.4581 0.5834
5.000 1.0056 0.01768 0.00877 -0.0940 0.4566 0.5873
5.250 1.0325 0.01787 0.00901 -0.0941 0.4554 0.5913
5.500 1.0595 0.01805 0.00926 -0.0942 0.4542 0.5948
5.750 1.0840 0.01831 0.00968 -0.0939 0.4525 0.5989
6.000 1.1082 0.01860 0.01011 -0.0937 0.4507 0.6036
6.250 1.1327 0.01887 0.01055 -0.0934 0.4489 0.6084
6.500 1.1572 0.01914 0.01096 -0.0932 0.4472 0.6138
6.750 1.1820 0.01941 0.01135 -0.0929 0.4456 0.6203
7.000 1.2068 0.01965 0.01174 -0.0927 0.4441 0.6271
7.250 1.2321 0.01988 0.01211 -0.0926 0.4427 0.6359
7.500 1.2579 0.02008 0.01244 -0.0925 0.4412 0.6465
7.750 1.2847 0.02031 0.01280 -0.0926 0.4400 0.6599
8.000 1.3055 0.02070 0.01345 -0.0918 0.4380 0.6770
8.250 1.3227 0.02063 0.01364 -0.0901 0.4310 0.7021
8.500 1.3381 0.01979 0.01300 -0.0876 0.4167 0.7564
8.750 1.3581 0.01923 0.01281 -0.0863 0.4017 1.0000
9.000 1.3695 0.01916 0.01269 -0.0836 0.3830 1.0000
9.250 1.3704 0.01954 0.01306 -0.0793 0.3517 1.0000
9.750 1.3250 0.02307 0.01597 -0.0665 0.2528 1.0000
10.000 1.2965 0.02636 0.01912 -0.0621 0.2190 1.0000
10.250 1.2681 0.03064 0.02332 -0.0596 0.1932 1.0000
10.500 1.2467 0.03495 0.02760 -0.0583 0.1710 1.0000
10.750 1.2173 0.04023 0.03279 -0.0572 0.1457 1.0000
11.000 1.1969 0.04476 0.03727 -0.0563 0.1249 1.0000
11.250 1.1696 0.05006 0.04244 -0.0556 0.0973 1.0000
11.500 1.1427 0.05548 0.04769 -0.0550 0.0652 1.0000
11.750 1.1167 0.06112 0.05311 -0.0548 0.0301 1.0000
12.000 1.1108 0.06475 0.05671 -0.0548 0.0199 1.0000
12.250 1.1056 0.06839 0.06036 -0.0548 0.0136 1.0000
12.500 1.1037 0.07172 0.06374 -0.0549 0.0115 1.0000
12.750 1.1056 0.07466 0.06679 -0.0550 0.0103 1.0000
13.000 1.1080 0.07758 0.06981 -0.0552 0.0097 1.0000
13.250 1.1098 0.08058 0.07290 -0.0554 0.0091 1.0000
13.500 1.1107 0.08376 0.07618 -0.0557 0.0086 1.0000
13.750 1.1108 0.08709 0.07960 -0.0561 0.0082 1.0000
14.000 1.1099 0.09060 0.08321 -0.0566 0.0080 1.0000
14.250 1.1089 0.09417 0.08689 -0.0571 0.0077 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)