USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 200,000 Max Cl/Cd: 67.23 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usnps4-il-200000-n5.txt Download as CSV file: xf-usnps4-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2176 0.08890 0.08546 -0.0598 0.9682 0.0281
-7.250 -0.2051 0.08473 0.08128 -0.0652 0.9638 0.0295
-7.000 -0.1958 0.07957 0.07611 -0.0727 0.9546 0.0306
-6.750 -0.1720 0.07316 0.06961 -0.0831 0.9506 0.0309
-6.500 -0.1614 0.06876 0.06514 -0.0861 0.9420 0.0310
-6.000 -0.1305 0.05461 0.05067 -0.0942 0.9307 0.0214
-5.500 -0.0778 0.04800 0.04384 -0.1003 0.9241 0.0224
-5.250 -0.0598 0.04553 0.04125 -0.1005 0.9164 0.0235
-5.000 -0.0303 0.04093 0.03635 -0.1035 0.9123 0.0241
-4.750 0.0029 0.03603 0.03107 -0.1064 0.9099 0.0240
-4.500 0.0238 0.03232 0.02700 -0.1060 0.9018 0.0241
-4.250 0.0559 0.02747 0.02152 -0.1073 0.8982 0.0252
-4.000 0.0906 0.02448 0.01803 -0.1089 0.8957 0.0266
-3.750 0.1145 0.02311 0.01647 -0.1082 0.8875 0.0271
-3.500 0.1480 0.02137 0.01442 -0.1093 0.8831 0.0280
-3.250 0.1864 0.01962 0.01232 -0.1112 0.8801 0.0292
-3.000 0.2111 0.01854 0.01089 -0.1102 0.8703 0.0312
-2.750 0.2500 0.01759 0.00990 -0.1125 0.8658 0.0327
-2.500 0.2782 0.01688 0.00909 -0.1124 0.8558 0.0340
-2.250 0.3208 0.01592 0.00798 -0.1152 0.8503 0.0361
-2.000 0.3516 0.01531 0.00732 -0.1157 0.8392 0.0386
-1.750 0.3870 0.01481 0.00680 -0.1172 0.8286 0.0417
-1.500 0.4245 0.01423 0.00611 -0.1191 0.8172 0.0449
-1.250 0.4604 0.01376 0.00564 -0.1207 0.8034 0.0495
-1.000 0.4943 0.01344 0.00522 -0.1218 0.7873 0.0548
-0.750 0.5262 0.01314 0.00488 -0.1227 0.7693 0.0617
-0.500 0.5571 0.01293 0.00457 -0.1232 0.7495 0.0696
-0.250 0.5870 0.01282 0.00434 -0.1235 0.7287 0.0806
0.000 0.6147 0.01272 0.00417 -0.1234 0.7067 0.0977
0.250 0.6411 0.01252 0.00407 -0.1232 0.6838 0.1651
0.500 0.6691 0.01071 0.00426 -0.1229 0.6614 1.0000
0.750 0.6928 0.01091 0.00422 -0.1219 0.6378 1.0000
1.000 0.7160 0.01114 0.00422 -0.1208 0.6143 1.0000
1.250 0.7387 0.01137 0.00425 -0.1197 0.5912 1.0000
1.500 0.7610 0.01163 0.00431 -0.1185 0.5687 1.0000
1.750 0.7833 0.01189 0.00439 -0.1174 0.5465 1.0000
2.000 0.8053 0.01217 0.00449 -0.1162 0.5253 1.0000
2.250 0.8272 0.01246 0.00461 -0.1150 0.5052 1.0000
2.500 0.8493 0.01274 0.00475 -0.1139 0.4858 1.0000
2.750 0.8713 0.01304 0.00490 -0.1127 0.4675 1.0000
3.000 0.8931 0.01334 0.00507 -0.1116 0.4499 1.0000
3.250 0.9150 0.01364 0.00526 -0.1105 0.4336 1.0000
3.500 0.9369 0.01395 0.00546 -0.1094 0.4185 1.0000
3.750 0.9587 0.01426 0.00567 -0.1083 0.4039 1.0000
4.000 0.9802 0.01458 0.00590 -0.1072 0.3903 1.0000
4.250 1.0016 0.01491 0.00614 -0.1061 0.3778 1.0000
4.500 1.0231 0.01524 0.00640 -0.1049 0.3658 1.0000
4.750 1.0447 0.01556 0.00666 -0.1039 0.3544 1.0000
5.000 1.0657 0.01589 0.00694 -0.1027 0.3437 1.0000
5.250 1.0856 0.01625 0.00723 -0.1013 0.3337 1.0000
5.500 1.1065 0.01657 0.00754 -0.1001 0.3245 1.0000
5.750 1.1260 0.01694 0.00787 -0.0987 0.3160 1.0000
6.000 1.1464 0.01729 0.00820 -0.0975 0.3071 1.0000
6.250 1.1661 0.01769 0.00858 -0.0961 0.2991 1.0000
6.500 1.1861 0.01807 0.00895 -0.0949 0.2912 1.0000
6.750 1.2057 0.01848 0.00934 -0.0936 0.2846 1.0000
7.000 1.2259 0.01887 0.00975 -0.0924 0.2777 1.0000
7.250 1.2442 0.01935 0.01020 -0.0909 0.2715 1.0000
7.500 1.2646 0.01974 0.01064 -0.0898 0.2648 1.0000
7.750 1.2828 0.02022 0.01111 -0.0884 0.2587 1.0000
8.000 1.3020 0.02068 0.01160 -0.0871 0.2532 1.0000
8.250 1.3211 0.02114 0.01211 -0.0859 0.2477 1.0000
8.500 1.3384 0.02169 0.01266 -0.0844 0.2430 1.0000
8.750 1.3572 0.02218 0.01321 -0.0831 0.2382 1.0000
9.000 1.3754 0.02270 0.01379 -0.0818 0.2331 1.0000
9.250 1.3917 0.02330 0.01441 -0.0802 0.2285 1.0000
9.500 1.4092 0.02387 0.01504 -0.0789 0.2242 1.0000
9.750 1.4269 0.02444 0.01569 -0.0776 0.2199 1.0000
10.000 1.4431 0.02508 0.01639 -0.0761 0.2160 1.0000
10.250 1.4579 0.02581 0.01713 -0.0745 0.2127 1.0000
10.500 1.4751 0.02643 0.01787 -0.0732 0.2091 1.0000
10.750 1.4912 0.02710 0.01864 -0.0718 0.2052 1.0000
11.000 1.5057 0.02785 0.01946 -0.0702 0.2015 1.0000
11.250 1.5188 0.02871 0.02034 -0.0686 0.1984 1.0000
11.500 1.5343 0.02946 0.02122 -0.0672 0.1954 1.0000
11.750 1.5493 0.03025 0.02214 -0.0659 0.1923 1.0000
12.000 1.5630 0.03111 0.02312 -0.0644 0.1893 1.0000
12.250 1.5752 0.03206 0.02414 -0.0628 0.1864 1.0000
12.500 1.5860 0.03310 0.02523 -0.0611 0.1829 1.0000
12.750 1.5972 0.03408 0.02639 -0.0596 0.1779 1.0000
13.000 1.6050 0.03528 0.02766 -0.0578 0.1727 1.0000
13.250 1.6126 0.03655 0.02903 -0.0561 0.1676 1.0000
13.500 1.6211 0.03781 0.03044 -0.0546 0.1620 1.0000
13.750 1.6256 0.03940 0.03207 -0.0530 0.1573 1.0000
14.000 1.6337 0.04081 0.03365 -0.0517 0.1520 1.0000
14.250 1.6385 0.04253 0.03547 -0.0503 0.1464 1.0000
14.500 1.6421 0.04442 0.03747 -0.0491 0.1409 1.0000
14.750 1.6460 0.04639 0.03956 -0.0480 0.1344 1.0000
15.000 1.6471 0.04870 0.04197 -0.0469 0.1282 1.0000
15.250 1.6480 0.05114 0.04452 -0.0461 0.1210 1.0000
15.500 1.6474 0.05384 0.04733 -0.0454 0.1141 1.0000
15.750 1.6424 0.05714 0.05070 -0.0448 0.1063 1.0000
16.000 1.6368 0.06064 0.05429 -0.0445 0.0966 1.0000
16.250 1.6260 0.06493 0.05864 -0.0445 0.0859 1.0000
16.500 1.6100 0.07009 0.06384 -0.0448 0.0746 1.0000
16.750 1.5895 0.07604 0.06983 -0.0456 0.0642 1.0000
17.000 1.5672 0.08251 0.07637 -0.0469 0.0559 1.0000
17.250 1.5441 0.08935 0.08329 -0.0485 0.0494 1.0000
17.500 1.5209 0.09641 0.09047 -0.0506 0.0450 1.0000
|
Polar data table (+)
Polar graphs
<< Back to USNPS4 (smoothed) (usnps4-il)