USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 100,000 Max Cl/Cd: 55.54 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usnps4-il-100000.txt Download as CSV file: xf-usnps4-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: USNPS4 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3575 0.11538 0.11095 -0.0237 1.0000 0.0656
-7.750 -0.3774 0.11462 0.11029 -0.0221 1.0000 0.0659
-7.500 -0.3958 0.11350 0.10926 -0.0221 1.0000 0.0662
-7.250 -0.4075 0.11169 0.10749 -0.0248 1.0000 0.0664
-7.000 -0.4144 0.10943 0.10522 -0.0281 1.0000 0.0666
-6.750 -0.4114 0.10397 0.09988 -0.0229 1.0000 0.0675
-6.500 -0.4078 0.10066 0.09663 -0.0181 1.0000 0.0686
-6.250 -0.4079 0.09800 0.09400 -0.0162 1.0000 0.0699
-6.000 -0.4087 0.09539 0.09142 -0.0156 1.0000 0.0712
-5.750 -0.4086 0.09266 0.08873 -0.0159 1.0000 0.0729
-5.500 -0.4064 0.08976 0.08584 -0.0172 1.0000 0.0750
-5.250 -0.3980 0.08665 0.08266 -0.0219 1.0000 0.0783
-5.000 -0.3710 0.08173 0.07746 -0.0327 0.9976 0.0810
-4.750 -0.3499 0.07731 0.07318 -0.0325 0.9922 0.0836
-4.500 -0.2881 0.07420 0.06942 -0.0479 0.9822 0.0954
-4.250 -0.2705 0.06825 0.06375 -0.0479 0.9771 0.0979
-4.000 -0.2400 0.06491 0.06038 -0.0510 0.9694 0.1038
-3.750 -0.1928 0.06045 0.05563 -0.0592 0.9631 0.1143
-3.500 -0.1534 0.05748 0.05229 -0.0646 0.9536 0.1283
-3.250 -0.1225 0.05429 0.04916 -0.0669 0.9465 0.1376
-3.000 -0.0813 0.05120 0.04582 -0.0720 0.9392 0.1623
-2.750 -0.0496 0.04861 0.04321 -0.0742 0.9307 0.1831
-2.500 -0.0076 0.04611 0.04056 -0.0786 0.9246 0.2278
-1.750 0.1490 0.03787 0.03012 -0.0894 0.9017 0.1263
-1.500 0.2006 0.03433 0.02619 -0.0929 0.8970 0.1037
-1.250 0.2399 0.03273 0.02425 -0.0943 0.8878 0.1026
-1.000 0.2894 0.03093 0.02211 -0.0973 0.8820 0.1021
-0.750 0.3258 0.02977 0.02078 -0.0983 0.8717 0.1057
-0.500 0.3759 0.02813 0.01900 -0.1014 0.8666 0.1129
-0.250 0.4098 0.02708 0.01800 -0.1020 0.8554 0.1240
0.000 0.4596 0.02540 0.01641 -0.1051 0.8511 0.1421
0.250 0.4925 0.02433 0.01546 -0.1053 0.8395 0.1686
0.500 0.5406 0.02094 0.01413 -0.1072 0.8364 1.0000
0.750 0.5757 0.02042 0.01332 -0.1076 0.8243 1.0000
1.000 0.6185 0.01970 0.01239 -0.1096 0.8142 1.0000
1.250 0.6702 0.01876 0.01126 -0.1132 0.8059 1.0000
1.750 0.7500 0.01765 0.00985 -0.1163 0.7761 1.0000
2.000 0.7916 0.01717 0.00921 -0.1182 0.7589 1.0000
2.250 0.8227 0.01702 0.00893 -0.1183 0.7367 1.0000
2.500 0.8577 0.01687 0.00860 -0.1191 0.7143 1.0000
2.750 0.8875 0.01691 0.00847 -0.1191 0.6899 1.0000
3.000 0.9179 0.01701 0.00836 -0.1191 0.6654 1.0000
3.250 0.9426 0.01727 0.00845 -0.1182 0.6398 1.0000
3.500 0.9698 0.01755 0.00851 -0.1178 0.6159 1.0000
3.750 0.9924 0.01793 0.00874 -0.1166 0.5912 1.0000
4.000 1.0180 0.01833 0.00890 -0.1160 0.5694 1.0000
4.250 1.0394 0.01878 0.00926 -0.1147 0.5470 1.0000
4.500 1.0625 0.01925 0.00957 -0.1137 0.5266 1.0000
4.750 1.0861 0.01976 0.00991 -0.1129 0.5080 1.0000
5.000 1.1099 0.02030 0.01028 -0.1122 0.4906 1.0000
5.250 1.1326 0.02085 0.01074 -0.1113 0.4740 1.0000
5.500 1.1559 0.02142 0.01120 -0.1105 0.4585 1.0000
5.750 1.1783 0.02200 0.01170 -0.1096 0.4438 1.0000
6.000 1.2001 0.02259 0.01228 -0.1086 0.4299 1.0000
6.250 1.2222 0.02321 0.01288 -0.1077 0.4170 1.0000
6.500 1.2452 0.02387 0.01350 -0.1070 0.4053 1.0000
6.750 1.2707 0.02454 0.01405 -0.1068 0.3945 1.0000
7.000 1.2914 0.02518 0.01475 -0.1057 0.3835 1.0000
7.250 1.3133 0.02591 0.01551 -0.1048 0.3736 1.0000
7.500 1.3406 0.02664 0.01612 -0.1051 0.3648 1.0000
7.750 1.3584 0.02739 0.01705 -0.1035 0.3556 1.0000
8.000 1.3853 0.02818 0.01773 -0.1037 0.3476 1.0000
8.250 1.4024 0.02894 0.01868 -0.1020 0.3392 1.0000
8.500 1.4304 0.02980 0.01944 -0.1024 0.3322 1.0000
8.750 1.4460 0.03069 0.02058 -0.1005 0.3250 1.0000
9.000 1.4742 0.03153 0.02134 -0.1010 0.3187 1.0000
9.250 1.4888 0.03254 0.02259 -0.0990 0.3121 1.0000
9.500 1.5101 0.03339 0.02353 -0.0982 0.3058 1.0000
9.750 1.5346 0.03447 0.02464 -0.0982 0.3004 1.0000
10.000 1.5470 0.03561 0.02606 -0.0959 0.2950 1.0000
10.250 1.5695 0.03660 0.02711 -0.0954 0.2899 1.0000
10.500 1.5916 0.03783 0.02844 -0.0950 0.2851 1.0000
10.750 1.5992 0.03912 0.03004 -0.0920 0.2801 1.0000
11.000 1.6183 0.04020 0.03124 -0.0910 0.2755 1.0000
11.250 1.6485 0.04151 0.03253 -0.0921 0.2714 1.0000
11.500 1.6451 0.04325 0.03471 -0.0875 0.2678 1.0000
11.750 1.6517 0.04479 0.03651 -0.0847 0.2637 1.0000
12.000 1.6712 0.04592 0.03774 -0.0839 0.2595 1.0000
12.250 1.6936 0.04746 0.03936 -0.0838 0.2558 1.0000
12.500 1.6777 0.04973 0.04205 -0.0778 0.2531 1.0000
12.750 1.6655 0.05192 0.04453 -0.0726 0.2502 1.0000
13.000 1.6669 0.05365 0.04647 -0.0694 0.2469 1.0000
13.250 1.7146 0.05397 0.04670 -0.0728 0.2411 1.0000
13.500 1.6778 0.05688 0.04998 -0.0645 0.2395 1.0000
13.750 1.6375 0.06065 0.05408 -0.0573 0.2380 1.0000
14.000 1.5850 0.06604 0.05977 -0.0506 0.2371 1.0000
14.250 1.6090 0.06566 0.05944 -0.0500 0.2307 1.0000
14.500 1.5617 0.07176 0.06579 -0.0457 0.2300 1.0000
14.750 1.5208 0.07818 0.07240 -0.0432 0.2286 1.0000
15.000 1.4775 0.08600 0.08036 -0.0423 0.2272 1.0000
15.250 1.6946 0.06083 0.05441 -0.0459 0.1972 1.0000
15.500 1.6560 0.06561 0.05956 -0.0418 0.1957 1.0000
15.750 1.6115 0.07182 0.06609 -0.0389 0.1947 1.0000
16.000 1.5474 0.08161 0.07619 -0.0378 0.1956 1.0000
16.250 1.6278 0.07274 0.06712 -0.0369 0.1822 1.0000
16.500 1.5777 0.08089 0.07558 -0.0362 0.1818 1.0000
16.750 1.5080 0.09333 0.08827 -0.0381 0.1831 1.0000
17.000 1.5823 0.08353 0.07837 -0.0354 0.1689 1.0000
17.250 1.5275 0.09416 0.08926 -0.0376 0.1691 1.0000
17.500 1.0348 0.21297 0.20727 -0.1058 0.2212 1.0000
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