FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 38-153 AIRFOIL (fx38153-il) Reynolds number: 100,000 Max Cl/Cd: 36.07 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx38153-il-100000-n5.txt Download as CSV file: xf-fx38153-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5461 0.09770 0.09291 -0.0503 0.9995 0.0214
-10.500 -0.5601 0.09067 0.08582 -0.0548 0.9976 0.0211
-10.250 -0.5785 0.08439 0.07945 -0.0583 0.9953 0.0207
-10.000 -0.5986 0.07895 0.07387 -0.0603 0.9926 0.0204
-9.750 -0.6197 0.07453 0.06930 -0.0602 0.9890 0.0202
-9.500 -0.6405 0.07088 0.06548 -0.0589 0.9855 0.0200
-9.250 -0.6591 0.06769 0.06209 -0.0570 0.9817 0.0199
-9.000 -0.6750 0.06456 0.05875 -0.0540 0.9772 0.0198
-8.750 -0.6824 0.06105 0.05496 -0.0520 0.9733 0.0198
-8.500 -0.6817 0.05724 0.05078 -0.0509 0.9699 0.0198
-8.250 -0.6830 0.05388 0.04706 -0.0484 0.9664 0.0196
-8.000 -0.6811 0.05067 0.04347 -0.0458 0.9628 0.0193
-7.750 -0.6711 0.04744 0.03979 -0.0442 0.9596 0.0191
-7.500 -0.6549 0.04448 0.03636 -0.0434 0.9572 0.0190
-7.250 -0.6344 0.04194 0.03338 -0.0430 0.9555 0.0190
-7.000 -0.6139 0.03986 0.03095 -0.0422 0.9535 0.0191
-6.750 -0.5972 0.03814 0.02897 -0.0406 0.9502 0.0192
-6.500 -0.5752 0.03657 0.02716 -0.0397 0.9475 0.0194
-6.250 -0.5506 0.03516 0.02556 -0.0393 0.9452 0.0198
-6.000 -0.5244 0.03392 0.02415 -0.0392 0.9433 0.0202
-5.750 -0.4975 0.03281 0.02292 -0.0392 0.9415 0.0208
-5.500 -0.4697 0.03182 0.02181 -0.0395 0.9399 0.0215
-5.250 -0.4545 0.03096 0.02088 -0.0375 0.9359 0.0222
-5.000 -0.4358 0.03015 0.02005 -0.0366 0.9325 0.0232
-4.750 -0.4118 0.02945 0.01929 -0.0365 0.9295 0.0247
-4.500 -0.3842 0.02883 0.01860 -0.0371 0.9270 0.0276
-4.250 -0.3537 0.02829 0.01802 -0.0382 0.9250 0.0343
-4.000 -0.3357 0.02765 0.01736 -0.0369 0.9201 0.0446
-3.750 -0.3122 0.02689 0.01679 -0.0367 0.9161 0.0751
-3.500 -0.2878 0.02531 0.01629 -0.0377 0.9135 0.2651
-3.250 -0.2827 0.02481 0.01788 -0.0312 0.9106 0.6230
-3.000 -0.2699 0.02605 0.01918 -0.0265 0.9050 0.7209
-2.750 -0.2494 0.02702 0.02002 -0.0242 0.9002 0.7560
-2.500 -0.2263 0.02803 0.02089 -0.0216 0.8966 0.7751
-2.250 -0.2061 0.02895 0.02171 -0.0184 0.8924 0.7941
-2.000 -0.1927 0.02954 0.02221 -0.0143 0.8856 0.8094
-1.750 -0.1661 0.02992 0.02246 -0.0131 0.8819 0.8217
-1.500 -0.1334 0.02996 0.02234 -0.0142 0.8794 0.8290
-1.250 -0.1217 0.02984 0.02214 -0.0117 0.8714 0.8345
-1.000 -0.0915 0.02973 0.02190 -0.0123 0.8675 0.8377
-0.750 -0.0557 0.02956 0.02160 -0.0142 0.8647 0.8412
-0.500 -0.0404 0.02936 0.02133 -0.0128 0.8554 0.8473
-0.250 -0.0089 0.02920 0.02107 -0.0135 0.8518 0.8499
0.000 0.0104 0.02910 0.02093 -0.0121 0.8447 0.8536
0.250 0.0391 0.02888 0.02064 -0.0127 0.8390 0.8568
0.500 0.0762 0.02857 0.02025 -0.0149 0.8357 0.8594
0.750 0.0936 0.02844 0.02008 -0.0137 0.8257 0.8631
1.000 0.1261 0.02816 0.01976 -0.0146 0.8219 0.8651
1.250 0.1441 0.02808 0.01967 -0.0132 0.8130 0.8681
1.500 0.1764 0.02776 0.01933 -0.0142 0.8079 0.8708
1.750 0.1995 0.02759 0.01916 -0.0138 0.7988 0.8741
2.000 0.2331 0.02725 0.01880 -0.0153 0.7932 0.8766
2.250 0.2562 0.02708 0.01865 -0.0147 0.7846 0.8788
2.500 0.2861 0.02672 0.01831 -0.0152 0.7785 0.8805
2.750 0.3106 0.02648 0.01810 -0.0148 0.7692 0.8824
3.000 0.3423 0.02600 0.01764 -0.0155 0.7625 0.8844
3.250 0.3660 0.02577 0.01746 -0.0150 0.7516 0.8868
3.500 0.4010 0.02518 0.01691 -0.0162 0.7458 0.8884
3.750 0.4257 0.02503 0.01680 -0.0161 0.7336 0.8903
4.000 0.4548 0.02471 0.01653 -0.0166 0.7216 0.8922
4.250 0.4824 0.02420 0.01607 -0.0162 0.7090 0.8939
4.500 0.5110 0.02373 0.01565 -0.0162 0.6942 0.8955
4.750 0.5424 0.02324 0.01520 -0.0166 0.6787 0.8968
5.000 0.5752 0.02276 0.01474 -0.0173 0.6625 0.8984
5.250 0.6078 0.02235 0.01437 -0.0180 0.6431 0.9001
5.500 0.6443 0.02189 0.01389 -0.0193 0.6213 0.9015
5.750 0.6774 0.02165 0.01362 -0.0202 0.5949 0.9029
6.000 0.7088 0.02155 0.01347 -0.0210 0.5654 0.9041
6.250 0.7391 0.02158 0.01343 -0.0216 0.5359 0.9054
6.500 0.7645 0.02178 0.01356 -0.0216 0.5045 0.9070
6.750 0.7845 0.02201 0.01369 -0.0204 0.4739 0.9088
7.000 0.8030 0.02236 0.01396 -0.0191 0.4439 0.9107
7.250 0.8216 0.02278 0.01432 -0.0181 0.4151 0.9123
7.500 0.8392 0.02328 0.01476 -0.0169 0.3853 0.9140
7.750 0.8552 0.02389 0.01526 -0.0157 0.3535 0.9157
8.000 0.8706 0.02457 0.01585 -0.0145 0.3212 0.9174
8.250 0.8850 0.02536 0.01650 -0.0132 0.2895 0.9193
8.500 0.9009 0.02615 0.01721 -0.0123 0.2600 0.9212
8.750 0.9136 0.02686 0.01786 -0.0106 0.2366 0.9232
9.000 0.9282 0.02758 0.01857 -0.0093 0.2180 0.9250
9.250 0.9443 0.02831 0.01933 -0.0084 0.2010 0.9267
9.500 0.9598 0.02911 0.02015 -0.0075 0.1864 0.9283
9.750 0.9752 0.02996 0.02103 -0.0066 0.1727 0.9300
10.000 0.9909 0.03084 0.02198 -0.0058 0.1580 0.9317
10.250 1.0061 0.03179 0.02296 -0.0051 0.1438 0.9335
10.500 1.0205 0.03278 0.02401 -0.0043 0.1329 0.9354
10.750 1.0306 0.03381 0.02506 -0.0028 0.1232 0.9375
11.000 1.0444 0.03471 0.02612 -0.0018 0.1116 0.9397
11.250 1.0563 0.03581 0.02731 -0.0007 0.1008 0.9418
11.500 1.0669 0.03709 0.02864 0.0003 0.0906 0.9437
11.750 1.0756 0.03856 0.03014 0.0013 0.0817 0.9455
12.000 1.0870 0.03992 0.03166 0.0020 0.0714 0.9474
12.250 1.0947 0.04151 0.03334 0.0031 0.0642 0.9493
12.500 1.0978 0.04333 0.03519 0.0045 0.0591 0.9517
12.750 1.1026 0.04513 0.03716 0.0057 0.0544 0.9543
13.000 1.1043 0.04729 0.03942 0.0068 0.0508 0.9570
13.250 1.1056 0.04964 0.04188 0.0077 0.0479 0.9596
13.500 1.1090 0.05187 0.04433 0.0084 0.0450 0.9621
13.750 1.1101 0.05427 0.04690 0.0091 0.0427 0.9646
14.000 1.1099 0.05695 0.04972 0.0095 0.0411 0.9674
14.250 1.1086 0.05987 0.05275 0.0097 0.0399 0.9703
14.750 1.1092 0.06569 0.05897 0.0096 0.0379 0.9769
15.000 1.1084 0.06879 0.06225 0.0093 0.0370 0.9816
15.250 1.1063 0.07195 0.06558 0.0088 0.0363 0.9902
15.500 1.1050 0.07534 0.06914 0.0079 0.0356 0.9999
15.750 1.1049 0.07902 0.07299 0.0067 0.0350 0.9999
16.000 1.1044 0.08283 0.07695 0.0053 0.0345 0.9999
16.250 1.1037 0.08673 0.08100 0.0038 0.0340 0.9999
16.500 1.1027 0.09071 0.08512 0.0022 0.0336 0.9999
16.750 1.1018 0.09470 0.08924 0.0006 0.0331 0.9999
17.000 1.0997 0.09897 0.09364 -0.0013 0.0326 0.9999
17.250 1.0912 0.10461 0.09955 -0.0043 0.0323 0.9999
17.500 1.0806 0.11083 0.10602 -0.0079 0.0320 0.9999
17.750 1.0671 0.11785 0.11330 -0.0122 0.0318 0.9999
18.000 1.0514 0.12561 0.12129 -0.0172 0.0316 0.9999
18.250 1.0323 0.13451 0.13040 -0.0232 0.0317 0.9999
18.500 1.0074 0.14533 0.14143 -0.0305 0.0319 0.9999
18.750 0.9705 0.16016 0.15643 -0.0404 0.0323 0.9999
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