FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 200,000 Max Cl/Cd: 47.39 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx38153-il-200000-n5.txt Download as CSV file: xf-fx38153-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4235 0.09263 0.08887 -0.0829 0.9783 0.0109
-11.500 -0.4448 0.08130 0.07748 -0.0905 0.9758 0.0106
-11.250 -0.4688 0.07285 0.06889 -0.0962 0.9732 0.0105
-11.000 -0.4908 0.06644 0.06229 -0.0994 0.9709 0.0103
-10.750 -0.5099 0.06104 0.05667 -0.1010 0.9691 0.0102
-10.500 -0.5355 0.05814 0.05364 -0.0971 0.9633 0.0101
-10.250 -0.5549 0.05455 0.04983 -0.0948 0.9593 0.0100
-10.000 -0.5700 0.05096 0.04596 -0.0926 0.9563 0.0099
-9.750 -0.5909 0.04878 0.04358 -0.0871 0.9507 0.0099
-9.500 -0.6050 0.04611 0.04064 -0.0825 0.9455 0.0098
-9.250 -0.6050 0.04284 0.03700 -0.0803 0.9425 0.0098
-9.000 -0.5958 0.03970 0.03346 -0.0792 0.9405 0.0099
-8.750 -0.5995 0.03798 0.03149 -0.0745 0.9360 0.0099
-8.500 -0.5948 0.03611 0.02933 -0.0712 0.9318 0.0100
-8.250 -0.5792 0.03426 0.02718 -0.0699 0.9295 0.0102
-8.000 -0.5594 0.03266 0.02528 -0.0692 0.9278 0.0107
-7.750 -0.5361 0.03105 0.02330 -0.0687 0.9267 0.0113
-7.500 -0.5104 0.02973 0.02180 -0.0689 0.9257 0.0116
-7.250 -0.4832 0.02855 0.02050 -0.0692 0.9248 0.0117
-7.000 -0.4826 0.02802 0.01990 -0.0643 0.9193 0.0118
-6.750 -0.4649 0.02721 0.01902 -0.0628 0.9167 0.0120
-6.500 -0.4431 0.02639 0.01812 -0.0621 0.9147 0.0121
-6.250 -0.4189 0.02558 0.01725 -0.0618 0.9130 0.0124
-6.000 -0.3933 0.02480 0.01640 -0.0619 0.9116 0.0127
-5.750 -0.3673 0.02406 0.01562 -0.0622 0.9104 0.0130
-5.500 -0.3593 0.02365 0.01514 -0.0588 0.9053 0.0133
-5.250 -0.3422 0.02313 0.01456 -0.0573 0.9013 0.0138
-5.000 -0.3176 0.02259 0.01394 -0.0572 0.8990 0.0145
-4.750 -0.2905 0.02201 0.01332 -0.0577 0.8973 0.0154
-4.500 -0.2611 0.02151 0.01272 -0.0585 0.8959 0.0173
-4.000 -0.2234 0.02083 0.01198 -0.0561 0.8884 0.0234
-3.750 -0.1973 0.02043 0.01163 -0.0563 0.8852 0.0405
-3.500 -0.1668 0.01996 0.01124 -0.0575 0.8831 0.0636
-3.250 -0.1350 0.01879 0.01071 -0.0598 0.8816 0.1999
-3.000 -0.1001 0.01657 0.01051 -0.0637 0.8810 0.6076
-2.750 -0.0813 0.01708 0.01130 -0.0603 0.8794 0.6828
-2.500 -0.0697 0.01748 0.01169 -0.0573 0.8717 0.7095
-2.250 -0.0379 0.01773 0.01186 -0.0579 0.8689 0.7388
-2.000 -0.0073 0.01800 0.01206 -0.0579 0.8667 0.7545
-1.750 0.0197 0.01826 0.01228 -0.0569 0.8650 0.7607
-1.500 0.0337 0.01864 0.01262 -0.0544 0.8567 0.7711
-1.250 0.0553 0.01899 0.01296 -0.0519 0.8533 0.7786
-1.000 0.0866 0.01904 0.01295 -0.0521 0.8511 0.7875
-0.750 0.0988 0.01934 0.01324 -0.0487 0.8429 0.7917
-0.500 0.1289 0.01922 0.01307 -0.0492 0.8395 0.7960
-0.250 0.1676 0.01891 0.01269 -0.0519 0.8375 0.8007
0.000 0.1991 0.01867 0.01242 -0.0524 0.8357 0.8021
0.250 0.2131 0.01883 0.01258 -0.0498 0.8260 0.8042
0.500 0.2452 0.01851 0.01224 -0.0506 0.8230 0.8057
0.750 0.2789 0.01816 0.01187 -0.0517 0.8209 0.8075
1.000 0.2975 0.01830 0.01201 -0.0504 0.8113 0.8103
1.250 0.3315 0.01792 0.01162 -0.0518 0.8079 0.8127
1.500 0.3626 0.01774 0.01142 -0.0531 0.8000 0.8162
1.750 0.3895 0.01744 0.01114 -0.0527 0.7933 0.8176
2.000 0.4123 0.01733 0.01105 -0.0516 0.7839 0.8192
2.500 0.4698 0.01678 0.01052 -0.0519 0.7644 0.8221
2.750 0.5002 0.01647 0.01022 -0.0524 0.7515 0.8235
3.000 0.5352 0.01603 0.00976 -0.0537 0.7362 0.8249
3.250 0.5736 0.01557 0.00926 -0.0556 0.7179 0.8263
3.500 0.6128 0.01520 0.00884 -0.0578 0.6965 0.8277
3.750 0.6529 0.01492 0.00843 -0.0602 0.6687 0.8288
4.000 0.6871 0.01489 0.00821 -0.0616 0.6293 0.8302
4.250 0.7159 0.01511 0.00819 -0.0623 0.5862 0.8320
4.500 0.7326 0.01546 0.00837 -0.0603 0.5465 0.8333
4.750 0.7475 0.01589 0.00862 -0.0580 0.5081 0.8348
5.000 0.7611 0.01642 0.00895 -0.0557 0.4662 0.8363
5.250 0.7748 0.01699 0.00932 -0.0536 0.4228 0.8379
5.500 0.7883 0.01763 0.00974 -0.0516 0.3782 0.8398
5.750 0.8033 0.01828 0.01019 -0.0499 0.3378 0.8418
6.000 0.8233 0.01878 0.01059 -0.0493 0.3066 0.8434
6.250 0.8444 0.01928 0.01100 -0.0489 0.2831 0.8449
6.750 0.8852 0.02040 0.01193 -0.0479 0.2316 0.8478
7.000 0.9016 0.02094 0.01241 -0.0465 0.2097 0.8491
7.250 0.9187 0.02151 0.01291 -0.0452 0.1875 0.8503
7.500 0.9365 0.02209 0.01345 -0.0441 0.1707 0.8515
7.750 0.9557 0.02262 0.01398 -0.0433 0.1545 0.8526
8.000 0.9742 0.02323 0.01454 -0.0425 0.1392 0.8539
8.250 0.9932 0.02383 0.01513 -0.0418 0.1277 0.8551
8.500 1.0129 0.02440 0.01574 -0.0412 0.1171 0.8564
8.750 1.0325 0.02501 0.01638 -0.0407 0.1057 0.8577
9.000 1.0513 0.02570 0.01707 -0.0401 0.0959 0.8592
9.250 1.0709 0.02638 0.01780 -0.0396 0.0884 0.8607
9.500 1.0900 0.02713 0.01858 -0.0392 0.0815 0.8622
9.750 1.1064 0.02779 0.01933 -0.0381 0.0699 0.8633
10.000 1.1193 0.02873 0.02022 -0.0366 0.0601 0.8643
10.250 1.1331 0.02962 0.02116 -0.0353 0.0530 0.8653
10.500 1.1469 0.03054 0.02215 -0.0340 0.0478 0.8664
10.750 1.1615 0.03142 0.02314 -0.0328 0.0397 0.8676
11.000 1.1731 0.03256 0.02430 -0.0315 0.0357 0.8688
11.250 1.1844 0.03377 0.02554 -0.0302 0.0327 0.8700
11.500 1.1962 0.03495 0.02686 -0.0290 0.0308 0.8713
11.750 1.2068 0.03626 0.02829 -0.0277 0.0291 0.8727
12.000 1.2158 0.03774 0.02987 -0.0265 0.0277 0.8743
12.250 1.2226 0.03946 0.03169 -0.0252 0.0264 0.8757
12.500 1.2323 0.04100 0.03337 -0.0243 0.0253 0.8770
12.750 1.2406 0.04250 0.03503 -0.0232 0.0241 0.8780
13.000 1.2471 0.04413 0.03682 -0.0219 0.0231 0.8791
13.250 1.2529 0.04590 0.03872 -0.0207 0.0221 0.8801
13.500 1.2579 0.04781 0.04076 -0.0197 0.0212 0.8812
13.750 1.2613 0.04994 0.04301 -0.0188 0.0205 0.8824
14.000 1.2658 0.05207 0.04529 -0.0182 0.0199 0.8836
14.250 1.2702 0.05430 0.04768 -0.0177 0.0192 0.8850
14.500 1.2736 0.05672 0.05025 -0.0173 0.0186 0.8864
14.750 1.2761 0.05936 0.05303 -0.0172 0.0181 0.8879
15.000 1.2774 0.06224 0.05607 -0.0173 0.0176 0.8893
15.250 1.2778 0.06537 0.05935 -0.0176 0.0172 0.8906
15.500 1.2766 0.06883 0.06294 -0.0182 0.0169 0.8917
15.750 1.2733 0.07257 0.06682 -0.0189 0.0166 0.8927
16.000 1.2682 0.07653 0.07091 -0.0197 0.0163 0.8936
16.250 1.2633 0.08060 0.07516 -0.0206 0.0160 0.8947
16.500 1.2575 0.08495 0.07968 -0.0219 0.0157 0.8957
16.750 1.2508 0.08957 0.08447 -0.0234 0.0154 0.8967
17.000 1.2430 0.09451 0.08957 -0.0253 0.0152 0.8978
17.250 1.2345 0.09965 0.09488 -0.0274 0.0149 0.8988
17.500 1.2252 0.10511 0.10049 -0.0299 0.0146 0.8999
17.750 1.2153 0.11080 0.10634 -0.0327 0.0144 0.9010
18.000 1.2046 0.11680 0.11248 -0.0358 0.0141 0.9021
18.250 1.1937 0.12295 0.11877 -0.0391 0.0139 0.9033
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