FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.47 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx38153-il-1000000.txt Download as CSV file: xf-fx38153-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1825 0.08507 0.08327 -0.1164 0.9695 0.0128
-12.250 -0.1924 0.07868 0.07690 -0.1188 0.9685 0.0130
-12.000 -0.2117 0.06935 0.06758 -0.1229 0.9675 0.0130
-11.750 -0.2815 0.05076 0.04880 -0.1329 0.9659 0.0123
-11.500 -0.3156 0.04385 0.04175 -0.1347 0.9634 0.0122
-11.250 -0.3378 0.03939 0.03716 -0.1347 0.9608 0.0122
-11.000 -0.3570 0.03562 0.03326 -0.1339 0.9584 0.0122
-10.750 -0.3717 0.03267 0.03018 -0.1325 0.9558 0.0123
-10.500 -0.3837 0.03025 0.02764 -0.1306 0.9529 0.0124
-10.250 -0.3932 0.02807 0.02535 -0.1283 0.9497 0.0127
-10.000 -0.4010 0.02599 0.02312 -0.1258 0.9461 0.0130
-9.750 -0.4521 0.03690 0.03369 -0.1233 0.9444 0.0127
-9.500 -0.4522 0.03601 0.03227 -0.1196 0.9414 0.0144
-9.250 -0.4506 0.03471 0.03064 -0.1169 0.9386 0.0145
-8.750 -0.4366 0.02121 0.01625 -0.1114 0.9346 0.0095
-8.500 -0.4068 0.01827 0.01307 -0.1107 0.9344 0.0080
-8.250 -0.3810 0.01699 0.01167 -0.1105 0.9333 0.0080
-8.000 -0.3605 0.01624 0.01086 -0.1096 0.9317 0.0081
-7.750 -0.3410 0.01561 0.01016 -0.1085 0.9300 0.0082
-7.500 -0.3215 0.01504 0.00954 -0.1074 0.9283 0.0083
-7.250 -0.3014 0.01450 0.00895 -0.1065 0.9268 0.0084
-7.000 -0.2802 0.01402 0.00842 -0.1058 0.9251 0.0085
-6.750 -0.2623 0.01364 0.00801 -0.1045 0.9229 0.0085
-6.500 -0.2449 0.01330 0.00763 -0.1031 0.9204 0.0086
-6.250 -0.2253 0.01294 0.00724 -0.1020 0.9180 0.0086
-6.000 -0.2029 0.01258 0.00685 -0.1015 0.9160 0.0087
-5.750 -0.1786 0.01226 0.00650 -0.1013 0.9144 0.0089
-5.500 -0.1536 0.01191 0.00612 -0.1012 0.9131 0.0091
-5.250 -0.1269 0.01162 0.00580 -0.1014 0.9119 0.0093
-5.000 -0.0989 0.01136 0.00552 -0.1019 0.9108 0.0095
-4.750 -0.0712 0.01118 0.00532 -0.1022 0.9091 0.0097
-4.500 -0.0507 0.01099 0.00514 -0.1010 0.9057 0.0101
-4.250 -0.0255 0.01077 0.00493 -0.1008 0.9028 0.0109
-4.000 0.0028 0.01052 0.00469 -0.1012 0.9005 0.0137
-3.750 0.0334 0.01026 0.00441 -0.1020 0.8985 0.0160
-3.500 0.0654 0.01001 0.00415 -0.1031 0.8968 0.0180
-3.250 0.0970 0.00982 0.00395 -0.1042 0.8952 0.0198
-3.000 0.1223 0.00967 0.00382 -0.1040 0.8924 0.0227
-2.750 0.1463 0.00944 0.00365 -0.1035 0.8883 0.0388
-2.500 0.1766 0.00905 0.00333 -0.1043 0.8842 0.0659
-2.250 0.2091 0.00859 0.00300 -0.1056 0.8806 0.1143
-2.000 0.2330 0.00787 0.00272 -0.1057 0.8755 0.2500
-1.750 0.2728 0.00590 0.00204 -0.1110 0.8702 0.6158
-1.500 0.3090 0.00556 0.00199 -0.1130 0.8657 0.7092
-1.250 0.3371 0.00556 0.00200 -0.1132 0.8606 0.7231
-1.000 0.3653 0.00558 0.00204 -0.1134 0.8560 0.7325
-0.750 0.3962 0.00557 0.00200 -0.1141 0.8516 0.7408
-0.500 0.4227 0.00562 0.00206 -0.1139 0.8429 0.7484
-0.250 0.4512 0.00566 0.00206 -0.1140 0.8320 0.7562
0.000 0.4771 0.00578 0.00217 -0.1135 0.8205 0.7626
0.250 0.5041 0.00587 0.00222 -0.1134 0.8069 0.7670
0.500 0.5314 0.00595 0.00222 -0.1134 0.7900 0.7701
0.750 0.5552 0.00607 0.00228 -0.1125 0.7681 0.7726
1.000 0.5750 0.00633 0.00242 -0.1108 0.7357 0.7755
1.250 0.5903 0.00674 0.00265 -0.1080 0.6927 0.7799
1.500 0.6038 0.00723 0.00290 -0.1051 0.6433 0.7843
1.750 0.6125 0.00769 0.00313 -0.1012 0.5904 0.7872
2.000 0.6207 0.00821 0.00342 -0.0972 0.5353 0.7894
2.250 0.6346 0.00871 0.00370 -0.0946 0.4833 0.7914
2.500 0.6512 0.00924 0.00397 -0.0927 0.4279 0.7930
2.750 0.6703 0.00973 0.00423 -0.0913 0.3782 0.7946
3.000 0.6908 0.01019 0.00447 -0.0903 0.3353 0.7962
3.250 0.7123 0.01064 0.00471 -0.0895 0.2920 0.7977
3.500 0.7342 0.01106 0.00495 -0.0888 0.2548 0.7990
3.750 0.7562 0.01149 0.00521 -0.0882 0.2221 0.8001
4.000 0.7777 0.01192 0.00546 -0.0874 0.1854 0.8013
4.250 0.8002 0.01225 0.00568 -0.0868 0.1640 0.8024
4.500 0.8215 0.01265 0.00596 -0.0860 0.1364 0.8034
4.750 0.8441 0.01297 0.00621 -0.0854 0.1231 0.8044
5.000 0.8657 0.01334 0.00650 -0.0845 0.1021 0.8055
5.250 0.8866 0.01376 0.00683 -0.0836 0.0852 0.8066
5.500 0.9093 0.01408 0.00711 -0.0831 0.0707 0.8077
5.750 0.9298 0.01455 0.00748 -0.0821 0.0548 0.8089
6.000 0.9527 0.01488 0.00778 -0.0816 0.0485 0.8101
6.250 0.9746 0.01527 0.00813 -0.0810 0.0362 0.8112
6.500 0.9966 0.01566 0.00848 -0.0803 0.0306 0.8123
6.750 1.0195 0.01599 0.00880 -0.0799 0.0289 0.8133
7.000 1.0424 0.01631 0.00913 -0.0794 0.0274 0.8143
7.250 1.0652 0.01663 0.00947 -0.0789 0.0261 0.8153
7.500 1.0880 0.01695 0.00982 -0.0785 0.0249 0.8161
8.000 1.1292 0.01781 0.01066 -0.0769 0.0163 0.8183
8.250 1.1495 0.01822 0.01109 -0.0760 0.0158 0.8192
8.500 1.1696 0.01865 0.01156 -0.0751 0.0155 0.8200
8.750 1.1892 0.01912 0.01205 -0.0742 0.0150 0.8209
9.000 1.2084 0.01961 0.01258 -0.0732 0.0146 0.8218
9.250 1.2270 0.02014 0.01313 -0.0721 0.0141 0.8228
9.500 1.2454 0.02068 0.01372 -0.0710 0.0136 0.8237
9.750 1.2635 0.02126 0.01434 -0.0699 0.0133 0.8247
10.000 1.2812 0.02186 0.01499 -0.0688 0.0130 0.8257
10.250 1.2985 0.02248 0.01566 -0.0676 0.0128 0.8267
10.500 1.3154 0.02312 0.01636 -0.0664 0.0126 0.8278
10.750 1.3318 0.02381 0.01711 -0.0652 0.0123 0.8289
11.000 1.3472 0.02457 0.01791 -0.0639 0.0121 0.8299
11.250 1.3618 0.02538 0.01878 -0.0625 0.0117 0.8308
11.500 1.3754 0.02627 0.01973 -0.0610 0.0113 0.8315
11.750 1.3872 0.02727 0.02080 -0.0594 0.0110 0.8322
12.000 1.3978 0.02838 0.02198 -0.0577 0.0106 0.8334
12.250 1.4055 0.02967 0.02336 -0.0556 0.0102 0.8344
12.500 1.4189 0.03055 0.02431 -0.0543 0.0099 0.8353
12.750 1.4343 0.03129 0.02511 -0.0533 0.0097 0.8362
13.000 1.4495 0.03205 0.02592 -0.0523 0.0092 0.8371
13.250 1.4631 0.03296 0.02689 -0.0512 0.0087 0.8380
13.500 1.4768 0.03388 0.02784 -0.0502 0.0080 0.8390
13.750 1.4842 0.03531 0.02934 -0.0486 0.0074 0.8400
14.000 1.5049 0.03567 0.02972 -0.0484 0.0068 0.8412
14.250 1.5203 0.03648 0.03058 -0.0476 0.0057 0.8424
14.500 1.5328 0.03755 0.03162 -0.0467 0.0035 0.8435
14.750 1.5398 0.03912 0.03320 -0.0454 0.0031 0.8446
15.000 1.5453 0.04088 0.03502 -0.0440 0.0027 0.8455
15.250 1.5510 0.04269 0.03689 -0.0428 0.0025 0.8463
15.500 1.5554 0.04465 0.03894 -0.0416 0.0025 0.8470
15.750 1.5587 0.04679 0.04118 -0.0406 0.0024 0.8480
16.000 1.5606 0.04913 0.04363 -0.0396 0.0023 0.8491
16.250 1.5613 0.05167 0.04630 -0.0387 0.0023 0.8502
16.500 1.5606 0.05445 0.04919 -0.0380 0.0022 0.8513
16.750 1.5586 0.05746 0.05233 -0.0374 0.0022 0.8524
17.000 1.5562 0.06062 0.05561 -0.0371 0.0022 0.8534
17.250 1.5519 0.06414 0.05926 -0.0370 0.0021 0.8544
17.500 1.5462 0.06799 0.06323 -0.0372 0.0021 0.8554
17.750 1.5393 0.07212 0.06750 -0.0376 0.0021 0.8563
18.000 1.5302 0.07666 0.07217 -0.0384 0.0021 0.8572
18.250 1.5190 0.08165 0.07729 -0.0395 0.0020 0.8581
18.500 1.5071 0.08689 0.08267 -0.0409 0.0020 0.8589
18.750 1.4939 0.09248 0.08840 -0.0427 0.0020 0.8596
19.000 1.4780 0.09862 0.09467 -0.0449 0.0020 0.8603
19.250 1.4614 0.10498 0.10118 -0.0474 0.0020 0.8609
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