FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 500,000 Max Cl/Cd: 60.76 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx38153-il-500000-n5.txt Download as CSV file: xf-fx38153-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5175 0.04621 0.04269 -0.1277 0.9617 0.0053
-12.000 -0.5410 0.04111 0.03723 -0.1268 0.9585 0.0053
-11.750 -0.5523 0.03749 0.03330 -0.1254 0.9560 0.0053
-11.500 -0.5569 0.03471 0.03025 -0.1239 0.9536 0.0053
-11.250 -0.5586 0.03253 0.02784 -0.1218 0.9505 0.0053
-11.000 -0.5557 0.03055 0.02563 -0.1199 0.9474 0.0054
-10.750 -0.5483 0.02882 0.02368 -0.1184 0.9449 0.0054
-10.500 -0.5373 0.02724 0.02191 -0.1171 0.9430 0.0055
-10.250 -0.5233 0.02582 0.02028 -0.1161 0.9414 0.0056
-10.000 -0.5068 0.02455 0.01884 -0.1152 0.9399 0.0057
-9.750 -0.4915 0.02351 0.01766 -0.1139 0.9378 0.0058
-9.500 -0.4756 0.02258 0.01660 -0.1126 0.9356 0.0059
-9.250 -0.4583 0.02173 0.01563 -0.1114 0.9334 0.0060
-9.000 -0.4396 0.02090 0.01469 -0.1105 0.9314 0.0061
-8.750 -0.4198 0.02013 0.01381 -0.1097 0.9296 0.0062
-8.500 -0.3996 0.01941 0.01301 -0.1089 0.9282 0.0063
-8.250 -0.3789 0.01873 0.01225 -0.1083 0.9268 0.0064
-8.000 -0.3580 0.01809 0.01154 -0.1076 0.9256 0.0065
-7.750 -0.3366 0.01753 0.01091 -0.1071 0.9243 0.0066
-7.500 -0.3259 0.01725 0.01059 -0.1044 0.9207 0.0068
-7.250 -0.3142 0.01682 0.01012 -0.1019 0.9176 0.0070
-7.000 -0.2986 0.01632 0.00959 -0.1002 0.9153 0.0072
-6.750 -0.2788 0.01584 0.00907 -0.0993 0.9134 0.0073
-6.500 -0.2563 0.01539 0.00857 -0.0989 0.9119 0.0073
-6.250 -0.2323 0.01497 0.00810 -0.0987 0.9107 0.0074
-6.000 -0.2071 0.01458 0.00767 -0.0988 0.9096 0.0075
-5.750 -0.1978 0.01448 0.00756 -0.0956 0.9053 0.0076
-5.500 -0.1802 0.01426 0.00731 -0.0940 0.9023 0.0077
-5.250 -0.1575 0.01399 0.00701 -0.0934 0.9002 0.0078
-5.000 -0.1328 0.01372 0.00671 -0.0932 0.8986 0.0080
-4.750 -0.1068 0.01346 0.00643 -0.0933 0.8974 0.0082
-4.500 -0.0794 0.01321 0.00616 -0.0936 0.8963 0.0086
-4.250 -0.0505 0.01295 0.00590 -0.0943 0.8953 0.0094
-4.000 -0.0200 0.01270 0.00566 -0.0952 0.8943 0.0143
-3.750 -0.0137 0.01272 0.00568 -0.0911 0.8877 0.0157
-3.500 0.0125 0.01254 0.00547 -0.0910 0.8852 0.0175
-3.250 0.0412 0.01231 0.00524 -0.0916 0.8833 0.0198
-3.000 0.0724 0.01197 0.00495 -0.0926 0.8816 0.0306
-2.750 0.1064 0.01166 0.00466 -0.0942 0.8800 0.0436
-2.500 0.1205 0.01147 0.00457 -0.0917 0.8739 0.0708
-2.250 0.1445 0.01087 0.00429 -0.0917 0.8700 0.1618
-2.000 0.1779 0.00924 0.00367 -0.0951 0.8676 0.4404
-1.750 0.2210 0.00811 0.00349 -0.0998 0.8661 0.6769
-1.500 0.2501 0.00811 0.00355 -0.1001 0.8635 0.7022
-1.250 0.2717 0.00821 0.00368 -0.0988 0.8579 0.7176
-1.000 0.3015 0.00818 0.00365 -0.0992 0.8536 0.7298
-0.750 0.3320 0.00810 0.00354 -0.0998 0.8472 0.7406
-0.500 0.3580 0.00811 0.00353 -0.0993 0.8374 0.7504
-0.250 0.3826 0.00815 0.00356 -0.0985 0.8267 0.7571
0.000 0.4097 0.00818 0.00358 -0.0983 0.8162 0.7619
0.250 0.4406 0.00818 0.00352 -0.0990 0.8029 0.7684
0.500 0.4678 0.00824 0.00353 -0.0987 0.7855 0.7720
0.750 0.4955 0.00831 0.00348 -0.0986 0.7589 0.7741
1.000 0.5177 0.00852 0.00343 -0.0973 0.7069 0.7757
1.250 0.5297 0.00896 0.00355 -0.0941 0.6471 0.7779
1.500 0.5393 0.00941 0.00372 -0.0905 0.5939 0.7805
1.750 0.5544 0.00982 0.00390 -0.0883 0.5477 0.7830
2.000 0.5737 0.01020 0.00407 -0.0870 0.5092 0.7851
2.250 0.5926 0.01055 0.00429 -0.0855 0.4779 0.7861
2.500 0.6141 0.01085 0.00449 -0.0845 0.4523 0.7872
2.750 0.6343 0.01122 0.00473 -0.0834 0.4213 0.7884
3.000 0.6530 0.01170 0.00502 -0.0820 0.3798 0.7896
3.250 0.6711 0.01225 0.00532 -0.0806 0.3316 0.7908
3.500 0.6904 0.01278 0.00562 -0.0794 0.2847 0.7920
3.750 0.7117 0.01322 0.00590 -0.0787 0.2484 0.7933
4.000 0.7327 0.01370 0.00621 -0.0779 0.2145 0.7949
4.250 0.7535 0.01422 0.00653 -0.0771 0.1784 0.7963
4.500 0.7768 0.01459 0.00681 -0.0768 0.1574 0.7977
4.750 0.7993 0.01503 0.00712 -0.0763 0.1339 0.7992
5.000 0.8234 0.01538 0.00740 -0.0762 0.1225 0.8005
5.250 0.8466 0.01566 0.00768 -0.0757 0.1110 0.8013
5.500 0.8671 0.01611 0.00804 -0.0748 0.0933 0.8022
5.750 0.8885 0.01649 0.00838 -0.0741 0.0840 0.8030
6.000 0.9092 0.01693 0.00877 -0.0732 0.0655 0.8040
6.250 0.9296 0.01739 0.00919 -0.0723 0.0556 0.8050
6.500 0.9508 0.01781 0.00959 -0.0716 0.0497 0.8061
6.750 0.9733 0.01813 0.00994 -0.0711 0.0460 0.8072
7.000 0.9924 0.01870 0.01046 -0.0700 0.0319 0.8082
7.250 1.0136 0.01913 0.01090 -0.0694 0.0296 0.8092
7.500 1.0347 0.01956 0.01135 -0.0687 0.0276 0.8103
7.750 1.0561 0.01999 0.01180 -0.0681 0.0262 0.8114
8.000 1.0778 0.02038 0.01225 -0.0676 0.0254 0.8125
8.250 1.0992 0.02080 0.01272 -0.0670 0.0245 0.8135
8.500 1.1201 0.02125 0.01321 -0.0664 0.0222 0.8146
8.750 1.1382 0.02192 0.01387 -0.0654 0.0163 0.8156
9.000 1.1565 0.02253 0.01449 -0.0644 0.0156 0.8166
9.250 1.1736 0.02316 0.01516 -0.0631 0.0148 0.8176
9.500 1.1903 0.02382 0.01587 -0.0619 0.0140 0.8185
9.750 1.2074 0.02446 0.01657 -0.0607 0.0136 0.8194
10.000 1.2242 0.02513 0.01731 -0.0596 0.0133 0.8203
10.250 1.2403 0.02585 0.01809 -0.0583 0.0130 0.8212
10.500 1.2565 0.02657 0.01889 -0.0572 0.0129 0.8222
10.750 1.2719 0.02736 0.01976 -0.0559 0.0126 0.8232
11.000 1.2862 0.02821 0.02069 -0.0546 0.0122 0.8242
11.250 1.2998 0.02914 0.02171 -0.0533 0.0117 0.8252
11.500 1.3121 0.03017 0.02282 -0.0518 0.0113 0.8263
11.750 1.3234 0.03129 0.02402 -0.0503 0.0109 0.8273
12.000 1.3339 0.03248 0.02529 -0.0488 0.0106 0.8284
12.250 1.3433 0.03377 0.02668 -0.0472 0.0103 0.8296
12.500 1.3507 0.03526 0.02825 -0.0456 0.0101 0.8308
12.750 1.3628 0.03639 0.02947 -0.0445 0.0099 0.8319
13.000 1.3737 0.03758 0.03076 -0.0433 0.0097 0.8327
13.250 1.3835 0.03888 0.03216 -0.0420 0.0095 0.8336
13.500 1.3928 0.04026 0.03364 -0.0409 0.0092 0.8345
13.750 1.4012 0.04177 0.03526 -0.0397 0.0090 0.8354
14.000 1.4088 0.04339 0.03699 -0.0386 0.0087 0.8363
14.250 1.4157 0.04511 0.03881 -0.0376 0.0083 0.8372
14.500 1.4218 0.04696 0.04077 -0.0367 0.0079 0.8382
14.750 1.4266 0.04901 0.04291 -0.0358 0.0076 0.8393
15.000 1.4318 0.05109 0.04509 -0.0351 0.0073 0.8406
15.250 1.4395 0.05296 0.04707 -0.0346 0.0069 0.8418
15.500 1.4451 0.05512 0.04937 -0.0342 0.0064 0.8430
15.750 1.4483 0.05761 0.05201 -0.0339 0.0057 0.8441
16.000 1.4475 0.06067 0.05521 -0.0336 0.0044 0.8451
16.250 1.4564 0.06258 0.05713 -0.0338 0.0033 0.8461
16.500 1.4575 0.06554 0.06011 -0.0340 0.0029 0.8470
16.750 1.4539 0.06917 0.06382 -0.0343 0.0027 0.8478
17.000 1.4492 0.07303 0.06781 -0.0348 0.0025 0.8486
17.250 1.4421 0.07731 0.07223 -0.0355 0.0024 0.8494
17.500 1.4334 0.08199 0.07706 -0.0366 0.0024 0.8502
17.750 1.4234 0.08702 0.08223 -0.0380 0.0023 0.8510
18.000 1.4118 0.09243 0.08779 -0.0398 0.0023 0.8518
18.250 1.3983 0.09824 0.09376 -0.0419 0.0022 0.8525
18.500 1.3842 0.10428 0.09996 -0.0443 0.0022 0.8533
18.750 1.3696 0.11057 0.10640 -0.0470 0.0022 0.8540
19.000 1.3532 0.11732 0.11330 -0.0501 0.0022 0.8548
19.250 1.3373 0.12411 0.12024 -0.0535 0.0022 0.8557
|
Polar data table (+)
Polar graphs
<< Back to FX 38-153 AIRFOIL (fx38153-il)