FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 50,000 Max Cl/Cd: 26.56 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx38153-il-50000-n5.txt Download as CSV file: xf-fx38153-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 38-153 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5177 0.10821 0.10135 -0.0491 1.0001 0.0369
-10.500 -0.5333 0.10253 0.09570 -0.0509 1.0001 0.0363
-10.250 -0.5539 0.09711 0.09032 -0.0521 1.0001 0.0357
-10.000 -0.5784 0.09222 0.08541 -0.0523 1.0001 0.0352
-9.750 -0.6055 0.08798 0.08113 -0.0513 1.0001 0.0348
-9.500 -0.6342 0.08441 0.07750 -0.0490 1.0001 0.0344
-9.250 -0.6645 0.08149 0.07450 -0.0453 1.0001 0.0341
-9.000 -0.6941 0.07879 0.07169 -0.0410 1.0001 0.0337
-8.750 -0.7179 0.07545 0.06815 -0.0373 1.0001 0.0333
-8.500 -0.7368 0.07192 0.06434 -0.0336 1.0001 0.0328
-8.250 -0.7522 0.06831 0.06026 -0.0299 1.0001 0.0323
-8.000 -0.7553 0.06523 0.05694 -0.0272 1.0001 0.0323
-7.750 -0.7556 0.06216 0.05358 -0.0247 1.0001 0.0322
-7.500 -0.7528 0.05912 0.05021 -0.0224 1.0001 0.0321
-7.250 -0.7467 0.05616 0.04689 -0.0203 1.0001 0.0321
-7.000 -0.7375 0.05332 0.04362 -0.0184 1.0001 0.0322
-6.750 -0.7250 0.05066 0.04057 -0.0167 1.0001 0.0323
-6.500 -0.7101 0.04828 0.03791 -0.0153 1.0001 0.0327
-6.250 -0.6939 0.04637 0.03586 -0.0142 1.0001 0.0336
-6.000 -0.6764 0.04462 0.03388 -0.0130 1.0001 0.0349
-5.750 -0.6572 0.04293 0.03191 -0.0117 1.0001 0.0366
-5.500 -0.6363 0.04139 0.03000 -0.0103 1.0001 0.0382
-5.250 -0.6148 0.03999 0.02840 -0.0088 1.0001 0.0398
-5.000 -0.5939 0.03883 0.02721 -0.0074 1.0001 0.0415
-4.750 -0.5726 0.03790 0.02619 -0.0057 1.0001 0.0437
-4.500 -0.5450 0.03716 0.02522 -0.0050 0.9981 0.0469
-4.250 -0.5176 0.03639 0.02443 -0.0053 0.9950 0.0529
-4.000 -0.4909 0.03572 0.02365 -0.0056 0.9914 0.0670
-3.750 -0.4671 0.03467 0.02279 -0.0059 0.9876 0.0886
-3.500 -0.4436 0.03306 0.02162 -0.0062 0.9841 0.1384
-3.250 -0.4467 0.03167 0.02348 0.0024 0.9812 0.5841
-3.000 -0.4329 0.03401 0.02570 0.0082 0.9753 0.7537
-2.750 -0.4131 0.03745 0.02895 0.0162 0.9713 0.8246
-2.500 -0.3654 0.03955 0.03065 0.0172 0.9703 0.8743
-2.250 -0.3270 0.03980 0.03054 0.0152 0.9667 0.8904
-2.000 -0.2929 0.03967 0.03012 0.0132 0.9614 0.8972
-1.750 -0.2624 0.03967 0.02985 0.0116 0.9563 0.9057
-1.500 -0.2263 0.03959 0.02950 0.0091 0.9509 0.9112
-1.250 -0.1969 0.03948 0.02919 0.0077 0.9446 0.9168
-1.000 -0.1653 0.03953 0.02905 0.0058 0.9396 0.9224
-0.750 -0.1360 0.03937 0.02871 0.0044 0.9327 0.9267
-0.500 -0.1033 0.03939 0.02858 0.0023 0.9267 0.9317
-0.250 -0.0771 0.03931 0.02837 0.0016 0.9191 0.9366
0.000 -0.0391 0.03932 0.02824 -0.0015 0.9124 0.9396
0.250 -0.0090 0.03928 0.02811 -0.0030 0.9048 0.9433
0.500 0.0174 0.03925 0.02800 -0.0038 0.8972 0.9474
0.750 0.0472 0.03923 0.02790 -0.0053 0.8895 0.9505
1.000 0.0837 0.03922 0.02783 -0.0080 0.8819 0.9531
1.250 0.1120 0.03914 0.02771 -0.0091 0.8722 0.9565
1.500 0.1487 0.03909 0.02762 -0.0115 0.8652 0.9596
1.750 0.1716 0.03899 0.02752 -0.0116 0.8544 0.9628
2.000 0.2045 0.03896 0.02749 -0.0136 0.8460 0.9652
2.250 0.2377 0.03886 0.02741 -0.0154 0.8373 0.9676
2.750 0.2873 0.03857 0.02717 -0.0158 0.8151 0.9732
3.000 0.3264 0.03833 0.02698 -0.0184 0.8065 0.9749
3.250 0.3514 0.03824 0.02696 -0.0188 0.7942 0.9773
3.500 0.3772 0.03811 0.02690 -0.0192 0.7822 0.9796
3.750 0.4070 0.03784 0.02672 -0.0199 0.7708 0.9820
4.000 0.4423 0.03737 0.02634 -0.0214 0.7608 0.9841
4.250 0.4696 0.03714 0.02622 -0.0219 0.7470 0.9862
4.500 0.4969 0.03687 0.02608 -0.0221 0.7332 0.9884
4.750 0.5247 0.03652 0.02585 -0.0224 0.7192 0.9908
5.000 0.5534 0.03604 0.02549 -0.0225 0.7050 0.9932
5.250 0.5840 0.03539 0.02500 -0.0228 0.6903 0.9953
5.500 0.6145 0.03468 0.02444 -0.0229 0.6750 0.9972
5.750 0.6443 0.03397 0.02387 -0.0228 0.6587 0.9993
6.000 0.6677 0.03334 0.02337 -0.0216 0.6418 0.9999
6.250 0.6909 0.03266 0.02279 -0.0201 0.6240 0.9999
6.500 0.7188 0.03186 0.02210 -0.0193 0.6053 0.9999
6.750 0.7351 0.03154 0.02184 -0.0169 0.5822 0.9999
7.000 0.7597 0.03098 0.02131 -0.0156 0.5581 0.9999
7.250 0.7764 0.03082 0.02118 -0.0135 0.5337 0.9999
7.500 0.7968 0.03064 0.02102 -0.0119 0.5097 0.9999
7.750 0.8075 0.03076 0.02115 -0.0090 0.4845 0.9999
8.000 0.8200 0.03087 0.02120 -0.0064 0.4583 0.9999
8.250 0.8276 0.03118 0.02148 -0.0032 0.4316 0.9999
8.500 0.8361 0.03162 0.02189 -0.0005 0.4056 0.9999
8.750 0.8468 0.03217 0.02239 0.0018 0.3806 0.9999
9.000 0.8580 0.03286 0.02311 0.0037 0.3570 0.9999
9.250 0.8733 0.03358 0.02380 0.0050 0.3361 0.9999
9.500 0.8874 0.03447 0.02476 0.0062 0.3151 0.9999
9.750 0.9006 0.03543 0.02575 0.0075 0.2944 0.9999
10.000 0.9130 0.03647 0.02676 0.0087 0.2743 0.9999
10.250 0.9240 0.03765 0.02797 0.0098 0.2547 0.9999
10.500 0.9367 0.03887 0.02927 0.0107 0.2375 0.9999
10.750 0.9515 0.04011 0.03057 0.0113 0.2223 0.9999
11.000 0.9653 0.04146 0.03202 0.0120 0.2074 0.9999
11.250 0.9752 0.04295 0.03360 0.0128 0.1927 0.9999
11.500 0.9825 0.04456 0.03526 0.0137 0.1786 0.9999
11.750 0.9882 0.04633 0.03709 0.0146 0.1651 0.9999
12.000 0.9935 0.04825 0.03916 0.0153 0.1522 0.9999
12.250 1.0002 0.05025 0.04135 0.0158 0.1408 0.9999
12.500 1.0061 0.05239 0.04364 0.0163 0.1304 0.9999
12.750 1.0102 0.05464 0.04593 0.0167 0.1211 0.9999
13.000 1.0119 0.05724 0.04874 0.0169 0.1114 0.9999
13.250 1.0129 0.06003 0.05172 0.0170 0.1028 0.9999
13.500 1.0140 0.06272 0.05445 0.0169 0.0964 0.9999
13.750 1.0163 0.06587 0.05789 0.0167 0.0898 0.9999
14.000 1.0171 0.06889 0.06097 0.0164 0.0845 0.9999
14.250 1.0173 0.07241 0.06471 0.0159 0.0798 0.9999
14.500 1.0148 0.07640 0.06900 0.0151 0.0757 0.9999
14.750 1.0136 0.08005 0.07278 0.0142 0.0724 0.9999
15.000 1.0120 0.08395 0.07679 0.0131 0.0697 0.9999
15.250 1.0006 0.08964 0.08283 0.0110 0.0677 0.9999
15.500 0.9869 0.09587 0.08935 0.0083 0.0661 0.9999
15.750 0.9703 0.10294 0.09667 0.0048 0.0649 0.9999
16.000 0.9473 0.11171 0.10569 -0.0001 0.0644 0.9999
16.250 0.9041 0.12592 0.12015 -0.0086 0.0653 0.9999
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