USA 48 AIRFOIL (usa48-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 48 AIRFOIL (usa48-il) Reynolds number: 500,000 Max Cl/Cd: 85.06 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa48-il-500000.txt Download as CSV file: xf-usa48-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: USA 48 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7070 0.08310 0.08024 -0.0642 1.0000 0.0173
-14.750 -0.6407 0.09305 0.09043 -0.0573 1.0000 0.0178
-14.500 -0.8048 0.06052 0.05705 -0.0778 1.0000 0.0169
-14.250 -0.8274 0.05477 0.05112 -0.0805 1.0000 0.0169
-14.000 -0.8464 0.05014 0.04633 -0.0818 1.0000 0.0169
-13.750 -0.8642 0.04620 0.04225 -0.0821 1.0000 0.0170
-13.500 -0.8788 0.04300 0.03892 -0.0815 1.0000 0.0171
-13.250 -0.8854 0.04101 0.03689 -0.0803 1.0000 0.0174
-13.000 -0.8980 0.03865 0.03442 -0.0785 1.0000 0.0174
-12.750 -0.9066 0.03713 0.03283 -0.0762 1.0000 0.0176
-12.500 -0.9211 0.03552 0.03113 -0.0727 1.0000 0.0177
-12.250 -0.9377 0.03437 0.02990 -0.0679 1.0000 0.0178
-12.000 -0.9557 0.03375 0.02922 -0.0618 1.0000 0.0179
-11.750 -0.9552 0.03270 0.02807 -0.0590 0.9991 0.0181
-11.500 -0.9323 0.03150 0.02673 -0.0602 0.9962 0.0187
-11.250 -0.9086 0.03001 0.02507 -0.0615 0.9938 0.0193
-11.000 -0.8884 0.02849 0.02335 -0.0618 0.9901 0.0200
-10.750 -0.8650 0.02688 0.02151 -0.0625 0.9870 0.0206
-10.500 -0.8367 0.02579 0.02039 -0.0641 0.9848 0.0214
-10.250 -0.8063 0.02533 0.01990 -0.0655 0.9826 0.0222
-10.000 -0.7829 0.02474 0.01924 -0.0654 0.9780 0.0231
-9.750 -0.7538 0.02375 0.01811 -0.0665 0.9751 0.0241
-9.500 -0.7218 0.02256 0.01675 -0.0681 0.9731 0.0252
-9.250 -0.6855 0.02168 0.01588 -0.0707 0.9715 0.0263
-9.000 -0.6626 0.02123 0.01539 -0.0701 0.9647 0.0273
-8.750 -0.6283 0.02066 0.01472 -0.0718 0.9619 0.0290
-8.500 -0.5949 0.01984 0.01379 -0.0734 0.9601 0.0306
-8.250 -0.5604 0.01907 0.01305 -0.0754 0.9588 0.0321
-8.000 -0.5410 0.01861 0.01255 -0.0739 0.9517 0.0335
-7.750 -0.5080 0.01812 0.01199 -0.0752 0.9489 0.0354
-7.500 -0.4750 0.01717 0.01098 -0.0767 0.9470 0.0375
-7.250 -0.4401 0.01642 0.01025 -0.0785 0.9455 0.0395
-7.000 -0.4176 0.01592 0.00973 -0.0776 0.9391 0.0413
-6.750 -0.3854 0.01547 0.00922 -0.0786 0.9358 0.0432
-6.500 -0.3539 0.01443 0.00815 -0.0797 0.9333 0.0454
-6.250 -0.3183 0.01362 0.00735 -0.0817 0.9313 0.0479
-6.000 -0.2941 0.01312 0.00681 -0.0811 0.9241 0.0500
-5.750 -0.2590 0.01261 0.00626 -0.0827 0.9198 0.0518
-5.500 -0.2213 0.01195 0.00554 -0.0851 0.9165 0.0542
-5.250 -0.1951 0.01143 0.00499 -0.0848 0.9078 0.0566
-5.000 -0.1582 0.01096 0.00446 -0.0869 0.9017 0.0594
-4.750 -0.1298 0.01066 0.00409 -0.0870 0.8917 0.0617
-4.500 -0.0927 0.01033 0.00372 -0.0890 0.8842 0.0669
-4.250 -0.0687 0.00996 0.00348 -0.0882 0.8714 0.0936
-4.000 -0.0421 0.00969 0.00323 -0.0880 0.8585 0.1160
-3.750 -0.0196 0.00915 0.00297 -0.0872 0.8442 0.1962
-3.250 0.0312 0.00878 0.00267 -0.0861 0.8118 0.2524
-3.000 0.0558 0.00864 0.00254 -0.0854 0.7951 0.2778
-2.750 0.0800 0.00854 0.00245 -0.0846 0.7793 0.3049
-2.500 0.1040 0.00845 0.00238 -0.0838 0.7653 0.3322
-2.250 0.1284 0.00840 0.00232 -0.0831 0.7526 0.3570
-2.000 0.1521 0.00835 0.00227 -0.0822 0.7388 0.3822
-1.750 0.1751 0.00830 0.00222 -0.0812 0.7241 0.4086
-1.500 0.1975 0.00824 0.00217 -0.0800 0.7097 0.4383
-1.000 0.2395 0.00789 0.00209 -0.0772 0.6855 0.5289
-0.750 0.2584 0.00778 0.00225 -0.0752 0.6748 0.6223
-0.500 0.2819 0.00787 0.00232 -0.0741 0.6633 0.6516
-0.250 0.3059 0.00795 0.00237 -0.0732 0.6523 0.6698
0.000 0.3297 0.00804 0.00241 -0.0722 0.6412 0.6835
0.250 0.3531 0.00815 0.00245 -0.0711 0.6294 0.6955
0.500 0.3766 0.00820 0.00250 -0.0701 0.6176 0.7060
0.750 0.4002 0.00827 0.00254 -0.0691 0.6063 0.7152
1.000 0.4236 0.00836 0.00258 -0.0681 0.5953 0.7226
1.250 0.4475 0.00843 0.00261 -0.0672 0.5841 0.7288
1.500 0.4714 0.00849 0.00265 -0.0663 0.5734 0.7345
1.750 0.4947 0.00860 0.00270 -0.0653 0.5632 0.7411
2.000 0.5182 0.00865 0.00275 -0.0643 0.5522 0.7474
2.250 0.5412 0.00874 0.00281 -0.0633 0.5407 0.7542
2.500 0.5644 0.00883 0.00286 -0.0623 0.5314 0.7606
2.750 0.5876 0.00889 0.00293 -0.0613 0.5212 0.7676
3.000 0.6105 0.00899 0.00301 -0.0602 0.5111 0.7746
3.500 0.6545 0.00912 0.00315 -0.0578 0.4893 0.7915
3.750 0.6763 0.00917 0.00323 -0.0565 0.4779 0.7992
4.000 0.6967 0.00927 0.00331 -0.0550 0.4656 0.8071
4.250 0.7171 0.00934 0.00340 -0.0535 0.4534 0.8133
4.500 0.7377 0.00943 0.00349 -0.0520 0.4396 0.8198
4.750 0.7572 0.00955 0.00361 -0.0504 0.4235 0.8271
5.000 0.7765 0.00968 0.00375 -0.0487 0.4074 0.8376
5.250 0.7953 0.00982 0.00392 -0.0469 0.3904 0.8543
5.500 0.8261 0.01000 0.00422 -0.0478 0.3700 0.8974
5.750 0.8924 0.01055 0.00471 -0.0568 0.3403 0.9510
6.000 0.9433 0.01109 0.00514 -0.0624 0.3145 0.9967
6.250 0.9600 0.01145 0.00541 -0.0605 0.2956 1.0000
6.500 0.9733 0.01180 0.00566 -0.0578 0.2739 1.0000
6.750 0.9855 0.01224 0.00596 -0.0550 0.2487 1.0000
7.000 0.9980 0.01271 0.00630 -0.0523 0.2222 1.0000
7.250 1.0064 0.01338 0.00675 -0.0489 0.1833 1.0000
7.500 1.0152 0.01407 0.00725 -0.0458 0.1550 1.0000
7.750 1.0291 0.01456 0.00768 -0.0435 0.1459 1.0000
8.000 1.0445 0.01499 0.00809 -0.0415 0.1410 1.0000
8.250 1.0591 0.01547 0.00855 -0.0394 0.1360 1.0000
8.500 1.0760 0.01585 0.00897 -0.0378 0.1329 1.0000
8.750 1.0915 0.01630 0.00944 -0.0359 0.1295 1.0000
9.000 1.1051 0.01686 0.01000 -0.0339 0.1256 1.0000
9.250 1.1182 0.01746 0.01061 -0.0318 0.1217 1.0000
9.500 1.1365 0.01782 0.01104 -0.0305 0.1189 1.0000
9.750 1.1517 0.01835 0.01160 -0.0289 0.1143 1.0000
10.000 1.1616 0.01916 0.01240 -0.0266 0.1084 1.0000
10.250 1.1825 0.01943 0.01273 -0.0259 0.1007 1.0000
10.500 1.1892 0.02050 0.01350 -0.0234 0.0567 1.0000
10.750 1.1874 0.02211 0.01505 -0.0200 0.0420 1.0000
11.000 1.1913 0.02347 0.01643 -0.0175 0.0365 1.0000
11.250 1.1997 0.02461 0.01763 -0.0157 0.0336 1.0000
11.500 1.2034 0.02612 0.01918 -0.0136 0.0310 1.0000
11.750 1.2095 0.02753 0.02067 -0.0119 0.0290 1.0000
12.000 1.2169 0.02890 0.02212 -0.0104 0.0276 1.0000
12.250 1.2223 0.03050 0.02377 -0.0090 0.0263 1.0000
12.500 1.2203 0.03278 0.02612 -0.0074 0.0249 1.0000
12.750 1.2228 0.03479 0.02822 -0.0063 0.0241 1.0000
13.000 1.2293 0.03653 0.03004 -0.0054 0.0231 1.0000
13.250 1.2336 0.03851 0.03210 -0.0047 0.0223 1.0000
13.500 1.2357 0.04076 0.03442 -0.0040 0.0216 1.0000
13.750 1.2359 0.04326 0.03700 -0.0034 0.0211 1.0000
14.000 1.2326 0.04622 0.04003 -0.0030 0.0204 1.0000
14.250 1.2221 0.05002 0.04392 -0.0025 0.0199 1.0000
14.500 1.2230 0.05271 0.04670 -0.0024 0.0196 1.0000
14.750 1.2231 0.05555 0.04964 -0.0024 0.0192 1.0000
15.000 1.2246 0.05831 0.05249 -0.0025 0.0187 1.0000
15.250 1.2237 0.06138 0.05565 -0.0027 0.0183 1.0000
15.500 1.2220 0.06459 0.05893 -0.0030 0.0178 1.0000
15.750 1.2215 0.06772 0.06213 -0.0035 0.0173 1.0000
16.000 1.2197 0.07106 0.06554 -0.0040 0.0169 1.0000
16.250 1.2160 0.07462 0.06917 -0.0045 0.0168 1.0000
16.500 1.2102 0.07842 0.07302 -0.0051 0.0163 1.0000
16.750 1.2031 0.08216 0.07681 -0.0052 0.0160 1.0000
17.000 1.2036 0.08541 0.08016 -0.0060 0.0158 1.0000
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