US1000ROOT (us1000root-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: US1000ROOT (us1000root-il) Reynolds number: 100,000 Max Cl/Cd: 38.34 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-us1000root-il-100000.txt Download as CSV file: xf-us1000root-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: US1000ROOT
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7425 0.09877 0.09178 -0.0219 1.0000 0.0398
-14.500 -0.7455 0.09485 0.08780 -0.0231 1.0000 0.0402
-14.250 -0.7566 0.08973 0.08259 -0.0248 1.0000 0.0422
-14.000 -0.7631 0.08534 0.07811 -0.0262 1.0000 0.0428
-13.750 -0.7715 0.08072 0.07339 -0.0277 1.0000 0.0432
-13.500 -0.7857 0.07538 0.06795 -0.0295 1.0000 0.0444
-13.250 -0.8105 0.06871 0.06121 -0.0317 1.0000 0.0471
-13.000 -0.8363 0.06218 0.05463 -0.0338 1.0000 0.0502
-12.750 -0.8296 0.05996 0.05222 -0.0343 1.0000 0.0473
-12.500 -0.8682 0.05230 0.04455 -0.0364 1.0000 0.0534
-12.250 -0.8803 0.04816 0.04033 -0.0372 1.0000 0.0549
-12.000 -0.9098 0.04263 0.03488 -0.0378 1.0000 0.0657
-11.500 -0.9665 0.03394 0.02664 -0.0353 1.0000 0.1344
-11.250 -0.9894 0.03117 0.02417 -0.0321 1.0000 0.1748
-11.000 -1.0072 0.02959 0.02262 -0.0279 1.0000 0.2105
-10.750 -1.0251 0.02902 0.02208 -0.0219 1.0000 0.2313
-10.500 -1.0439 0.02894 0.02195 -0.0146 1.0000 0.2466
-10.250 -1.0513 0.02903 0.02203 -0.0090 1.0000 0.2601
-10.000 -1.0546 0.02957 0.02260 -0.0037 1.0000 0.2746
-9.750 -1.0506 0.03060 0.02373 0.0007 1.0000 0.2899
-9.500 -1.0372 0.03193 0.02519 0.0038 1.0000 0.3050
-9.250 -1.0396 0.03124 0.02430 0.0084 1.0000 0.3122
-9.000 -1.0144 0.03167 0.02482 0.0092 1.0000 0.3202
-8.750 -1.0243 0.03076 0.02367 0.0149 1.0000 0.3261
-8.500 -0.9978 0.03124 0.02433 0.0156 1.0000 0.3338
-8.250 -1.0083 0.03046 0.02330 0.0213 1.0000 0.3398
-8.000 -0.9873 0.03052 0.02349 0.0225 1.0000 0.3460
-7.750 -0.9844 0.03000 0.02284 0.0262 1.0000 0.3519
-7.500 -0.9807 0.02932 0.02201 0.0297 1.0000 0.3570
-7.250 -0.9654 0.02904 0.02175 0.0316 1.0000 0.3618
-7.000 -0.9620 0.02843 0.02095 0.0350 1.0000 0.3676
-6.750 -0.9513 0.02794 0.02039 0.0373 1.0000 0.3725
-6.500 -0.9375 0.02770 0.02013 0.0392 1.0000 0.3777
-6.250 -0.9336 0.02713 0.01929 0.0425 1.0000 0.3838
-6.000 -0.8835 0.02699 0.01921 0.0377 0.9913 0.3911
-5.750 -0.8431 0.02645 0.01841 0.0342 0.9805 0.3998
-5.500 -0.7935 0.02617 0.01818 0.0296 0.9712 0.4071
-5.250 -0.7547 0.02559 0.01739 0.0268 0.9597 0.4153
-5.000 -0.7103 0.02523 0.01705 0.0233 0.9491 0.4227
-4.750 -0.6681 0.02470 0.01641 0.0201 0.9385 0.4312
-4.500 -0.6175 0.02422 0.01588 0.0155 0.9297 0.4401
-4.250 -0.5751 0.02375 0.01540 0.0126 0.9182 0.4486
-4.000 -0.5323 0.02323 0.01475 0.0096 0.9078 0.4590
-3.750 -0.4718 0.02263 0.01421 0.0036 0.9008 0.4693
-3.500 -0.4252 0.02216 0.01375 0.0001 0.8893 0.4794
-3.250 -0.3805 0.02170 0.01327 -0.0030 0.8772 0.4910
-3.000 -0.3397 0.02129 0.01280 -0.0052 0.8639 0.5032
-2.750 -0.2992 0.02093 0.01250 -0.0073 0.8495 0.5143
-2.500 -0.2646 0.02064 0.01225 -0.0081 0.8337 0.5258
-2.250 -0.2341 0.02037 0.01198 -0.0081 0.8173 0.5378
-2.000 -0.2059 0.02012 0.01173 -0.0077 0.8009 0.5506
-1.750 -0.1786 0.01986 0.01145 -0.0071 0.7845 0.5638
-1.500 -0.1521 0.01961 0.01119 -0.0063 0.7684 0.5774
-1.250 -0.1289 0.01942 0.01101 -0.0049 0.7509 0.5915
-1.000 -0.1054 0.01925 0.01085 -0.0035 0.7334 0.6059
-0.750 -0.0802 0.01908 0.01070 -0.0024 0.7164 0.6207
-0.500 -0.0542 0.01896 0.01060 -0.0015 0.6999 0.6359
-0.250 -0.0277 0.01888 0.01053 -0.0006 0.6835 0.6516
0.000 -0.0010 0.01885 0.01051 0.0002 0.6674 0.6674
0.250 0.0257 0.01887 0.01053 0.0010 0.6515 0.6835
0.500 0.0522 0.01896 0.01060 0.0019 0.6360 0.6999
0.750 0.0781 0.01908 0.01071 0.0029 0.6209 0.7164
1.000 0.1033 0.01924 0.01086 0.0039 0.6060 0.7334
1.250 0.1269 0.01941 0.01101 0.0053 0.5916 0.7509
1.500 0.1500 0.01960 0.01119 0.0067 0.5776 0.7684
1.750 0.1767 0.01985 0.01146 0.0075 0.5639 0.7846
2.000 0.2039 0.02011 0.01173 0.0081 0.5508 0.8009
2.250 0.2323 0.02036 0.01198 0.0085 0.5380 0.8174
2.500 0.2628 0.02063 0.01224 0.0085 0.5258 0.8338
2.750 0.2976 0.02092 0.01250 0.0076 0.5144 0.8498
3.000 0.3378 0.02127 0.01281 0.0057 0.5033 0.8641
3.250 0.3788 0.02168 0.01327 0.0034 0.4911 0.8773
3.500 0.4238 0.02215 0.01376 0.0003 0.4795 0.8894
3.750 0.4706 0.02261 0.01421 -0.0033 0.4694 0.9009
4.000 0.5306 0.02320 0.01475 -0.0092 0.4590 0.9080
4.250 0.5742 0.02374 0.01541 -0.0124 0.4486 0.9184
4.500 0.6163 0.02419 0.01589 -0.0152 0.4401 0.9298
4.750 0.6664 0.02468 0.01643 -0.0197 0.4313 0.9387
5.000 0.7090 0.02521 0.01707 -0.0230 0.4228 0.9492
5.250 0.7539 0.02557 0.01741 -0.0265 0.4152 0.9600
5.500 0.7928 0.02615 0.01822 -0.0294 0.4071 0.9714
5.750 0.8405 0.02628 0.01830 -0.0336 0.3975 0.9812
6.000 0.8872 0.02602 0.01796 -0.0377 0.3839 0.9912
6.250 0.9274 0.02556 0.01750 -0.0407 0.3682 1.0000
6.500 0.9346 0.02565 0.01774 -0.0377 0.3598 1.0000
6.750 0.9506 0.02577 0.01780 -0.0361 0.3544 1.0000
7.000 0.9550 0.02606 0.01829 -0.0326 0.3471 1.0000
7.250 0.9683 0.02593 0.01807 -0.0304 0.3389 1.0000
7.500 0.9722 0.02611 0.01841 -0.0267 0.3312 1.0000
7.750 0.9860 0.02615 0.01839 -0.0245 0.3249 1.0000
8.000 0.9848 0.02592 0.01824 -0.0197 0.3135 1.0000
8.250 0.9854 0.02604 0.01843 -0.0154 0.3055 1.0000
8.500 0.9734 0.02539 0.01772 -0.0086 0.2881 1.0000
8.750 0.9656 0.02519 0.01751 -0.0027 0.2729 1.0000
9.000 0.9601 0.02522 0.01755 0.0028 0.2568 1.0000
9.250 0.9561 0.02547 0.01778 0.0079 0.2399 1.0000
9.500 0.9448 0.02590 0.01817 0.0141 0.2130 1.0000
9.750 0.9299 0.02678 0.01885 0.0202 0.1719 1.0000
10.000 0.9071 0.02865 0.02029 0.0260 0.1236 1.0000
10.250 0.8786 0.03158 0.02280 0.0307 0.0647 1.0000
10.500 0.8625 0.03427 0.02535 0.0334 0.0488 1.0000
10.750 0.8520 0.03690 0.02799 0.0351 0.0432 1.0000
11.000 0.8365 0.04031 0.03144 0.0363 0.0389 1.0000
11.250 0.8231 0.04394 0.03517 0.0366 0.0364 1.0000
11.500 0.8029 0.04870 0.04006 0.0362 0.0333 1.0000
11.750 0.7939 0.05257 0.04409 0.0354 0.0330 1.0000
12.000 0.7844 0.05670 0.04835 0.0344 0.0331 1.0000
12.250 0.7738 0.06113 0.05294 0.0332 0.0327 1.0000
12.500 0.7612 0.06595 0.05790 0.0318 0.0322 1.0000
12.750 0.7447 0.07143 0.06354 0.0300 0.0307 1.0000
13.000 0.7382 0.07564 0.06786 0.0287 0.0309 1.0000
13.250 0.7284 0.08041 0.07276 0.0272 0.0307 1.0000
13.500 0.7185 0.08528 0.07772 0.0256 0.0300 1.0000
13.750 0.7104 0.08993 0.08246 0.0241 0.0292 1.0000
14.000 0.7072 0.09387 0.08648 0.0229 0.0291 1.0000
14.250 0.7065 0.09744 0.09012 0.0218 0.0291 1.0000
|
Polar data table (+)
Polar graphs
<< Back to US1000ROOT (us1000root-il)