S1016 (s1016-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1016 (s1016-il) Reynolds number: 100,000 Max Cl/Cd: 23.54 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1016-il-100000-n5.txt Download as CSV file: xf-s1016-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1016
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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8259 0.10432 0.09836 -0.0542 1.0000 0.0596
-17.500 -0.8761 0.09169 0.08541 -0.0614 1.0000 0.0599
-17.250 -0.9044 0.08366 0.07710 -0.0656 1.0000 0.0607
-17.000 -0.9269 0.07701 0.07016 -0.0688 1.0000 0.0617
-16.750 -0.9408 0.07192 0.06484 -0.0709 1.0000 0.0628
-16.500 -0.9376 0.06939 0.06234 -0.0718 1.0000 0.0642
-16.250 -0.9393 0.06629 0.05917 -0.0728 1.0000 0.0657
-16.000 -0.9426 0.06306 0.05581 -0.0736 1.0000 0.0673
-15.750 -0.9470 0.05987 0.05244 -0.0743 1.0000 0.0691
-15.500 -0.9515 0.05676 0.04906 -0.0746 1.0000 0.0710
-15.250 -0.9497 0.05447 0.04670 -0.0746 1.0000 0.0728
-15.000 -0.9462 0.05258 0.04479 -0.0745 1.0000 0.0747
-14.750 -0.9440 0.05067 0.04279 -0.0741 1.0000 0.0769
-14.500 -0.9424 0.04881 0.04078 -0.0734 1.0000 0.0793
-14.250 -0.9424 0.04705 0.03880 -0.0722 1.0000 0.0817
-14.000 -0.9377 0.04570 0.03748 -0.0712 0.9969 0.0839
-13.750 -0.9267 0.04422 0.03592 -0.0715 0.9857 0.0867
-13.500 -0.9140 0.04271 0.03426 -0.0719 0.9800 0.0902
-13.250 -0.9001 0.04123 0.03260 -0.0723 0.9752 0.0938
-13.000 -0.8851 0.03996 0.03131 -0.0727 0.9715 0.0971
-12.750 -0.8688 0.03871 0.02996 -0.0731 0.9686 0.1012
-12.500 -0.8528 0.03755 0.02859 -0.0732 0.9655 0.1058
-12.250 -0.8374 0.03648 0.02755 -0.0731 0.9625 0.1096
-12.000 -0.8208 0.03548 0.02646 -0.0731 0.9598 0.1143
-11.750 -0.8024 0.03451 0.02536 -0.0732 0.9575 0.1197
-11.500 -0.7850 0.03358 0.02442 -0.0732 0.9554 0.1245
-11.250 -0.7668 0.03276 0.02349 -0.0731 0.9533 0.1304
-11.000 -0.7509 0.03199 0.02270 -0.0725 0.9508 0.1358
-10.750 -0.7353 0.03128 0.02196 -0.0718 0.9483 0.1418
-10.500 -0.7169 0.03063 0.02121 -0.0714 0.9462 0.1485
-10.250 -0.7005 0.02992 0.02053 -0.0708 0.9438 0.1552
-10.000 -0.6803 0.02933 0.01983 -0.0706 0.9418 0.1633
-9.750 -0.6624 0.02866 0.01921 -0.0701 0.9399 0.1709
-9.500 -0.6459 0.02820 0.01867 -0.0691 0.9379 0.1797
-9.250 -0.6332 0.02770 0.01823 -0.0676 0.9356 0.1880
-9.000 -0.6179 0.02729 0.01780 -0.0663 0.9334 0.1976
-8.750 -0.6035 0.02686 0.01739 -0.0650 0.9314 0.2079
-8.500 -0.5880 0.02643 0.01699 -0.0638 0.9295 0.2191
-8.250 -0.5704 0.02602 0.01658 -0.0628 0.9276 0.2319
-8.000 -0.5521 0.02559 0.01619 -0.0620 0.9258 0.2467
-7.750 -0.5339 0.02519 0.01582 -0.0612 0.9242 0.2627
-7.500 -0.5262 0.02497 0.01568 -0.0584 0.9219 0.2778
-7.250 -0.5187 0.02476 0.01555 -0.0555 0.9194 0.2945
-7.000 -0.5090 0.02453 0.01540 -0.0529 0.9166 0.3136
-6.750 -0.4976 0.02426 0.01524 -0.0506 0.9140 0.3355
-6.500 -0.4858 0.02401 0.01510 -0.0484 0.9120 0.3609
-6.250 -0.4714 0.02376 0.01499 -0.0465 0.9102 0.3895
-6.000 -0.4529 0.02351 0.01491 -0.0453 0.9085 0.4237
-5.750 -0.4570 0.02360 0.01516 -0.0398 0.9045 0.4500
-5.500 -0.4505 0.02365 0.01538 -0.0360 0.9014 0.4829
-5.250 -0.4286 0.02380 0.01575 -0.0346 0.8992 0.5242
-5.000 -0.3876 0.02442 0.01659 -0.0360 0.8984 0.5659
-4.750 -0.3471 0.02528 0.01755 -0.0371 0.8976 0.5983
-4.500 -0.3095 0.02614 0.01845 -0.0378 0.8965 0.6215
-4.250 -0.2783 0.02678 0.01906 -0.0378 0.8949 0.6407
-4.000 -0.2495 0.02731 0.01956 -0.0376 0.8933 0.6577
-3.750 -0.2405 0.02792 0.02016 -0.0339 0.8897 0.6723
-3.500 -0.2423 0.02848 0.02071 -0.0284 0.8843 0.6861
-3.000 -0.2104 0.02921 0.02135 -0.0240 0.8780 0.7143
-2.750 -0.2145 0.02956 0.02168 -0.0183 0.8729 0.7286
-2.500 -0.2364 0.02983 0.02195 -0.0093 0.8650 0.7434
-2.000 -0.1713 0.03069 0.02271 -0.0105 0.8605 0.7610
-1.750 -0.2092 0.03085 0.02287 0.0015 0.8499 0.7757
-1.500 -0.1572 0.03153 0.02353 -0.0024 0.8483 0.7797
-1.250 -0.1438 0.03150 0.02346 0.0002 0.8443 0.7919
-1.000 -0.0855 0.03196 0.02389 -0.0051 0.8435 0.7945
-0.750 -0.1221 0.03201 0.02395 0.0067 0.8315 0.8084
-0.500 -0.0677 0.03235 0.02427 0.0021 0.8296 0.8109
-0.250 -0.0104 0.03250 0.02442 -0.0032 0.8280 0.8132
0.000 -0.0424 0.03245 0.02437 0.0077 0.8162 0.8263
0.250 0.0105 0.03250 0.02442 0.0032 0.8132 0.8280
0.500 0.0679 0.03234 0.02427 -0.0021 0.8109 0.8296
0.750 0.1211 0.03203 0.02397 -0.0065 0.8083 0.8316
1.000 0.0854 0.03196 0.02389 0.0051 0.7945 0.8435
1.250 0.1442 0.03149 0.02345 -0.0002 0.7919 0.8443
1.500 0.1572 0.03152 0.02352 0.0024 0.7797 0.8483
1.750 0.1346 0.03122 0.02321 0.0117 0.7677 0.8581
2.000 0.1710 0.03069 0.02271 0.0105 0.7610 0.8605
2.250 0.1898 0.03051 0.02257 0.0122 0.7490 0.8636
2.500 0.2362 0.02983 0.02195 0.0093 0.7434 0.8650
3.000 0.2105 0.02920 0.02134 0.0240 0.7143 0.8780
3.250 0.2291 0.02888 0.02107 0.0257 0.7003 0.8808
3.500 0.2423 0.02847 0.02070 0.0284 0.6861 0.8844
3.750 0.2401 0.02791 0.02014 0.0340 0.6721 0.8898
4.000 0.2497 0.02730 0.01955 0.0375 0.6577 0.8934
4.250 0.2784 0.02677 0.01906 0.0377 0.6411 0.8949
4.500 0.3095 0.02614 0.01845 0.0378 0.6219 0.8966
4.750 0.3472 0.02527 0.01754 0.0370 0.5984 0.8977
5.000 0.3876 0.02441 0.01658 0.0360 0.5660 0.8984
5.250 0.4285 0.02379 0.01574 0.0347 0.5240 0.8992
5.500 0.4505 0.02364 0.01537 0.0360 0.4830 0.9014
5.750 0.4571 0.02359 0.01515 0.0397 0.4504 0.9046
6.000 0.4532 0.02350 0.01491 0.0452 0.4238 0.9085
6.250 0.4716 0.02375 0.01498 0.0465 0.3895 0.9102
6.500 0.4859 0.02400 0.01509 0.0484 0.3608 0.9120
6.750 0.4979 0.02425 0.01522 0.0506 0.3357 0.9140
7.000 0.5093 0.02452 0.01539 0.0529 0.3137 0.9166
7.250 0.5188 0.02476 0.01554 0.0555 0.2943 0.9194
7.500 0.5264 0.02496 0.01567 0.0583 0.2778 0.9219
7.750 0.5343 0.02518 0.01581 0.0611 0.2627 0.9243
8.000 0.5524 0.02559 0.01618 0.0620 0.2465 0.9258
8.250 0.5707 0.02601 0.01657 0.0628 0.2317 0.9277
8.500 0.5883 0.02642 0.01697 0.0637 0.2189 0.9296
8.750 0.6039 0.02685 0.01737 0.0649 0.2079 0.9315
9.000 0.6182 0.02728 0.01778 0.0663 0.1974 0.9335
9.250 0.6336 0.02769 0.01822 0.0675 0.1879 0.9356
9.500 0.6465 0.02819 0.01866 0.0691 0.1798 0.9379
9.750 0.6630 0.02865 0.01920 0.0700 0.1709 0.9400
10.000 0.6808 0.02932 0.01981 0.0705 0.1632 0.9418
10.250 0.7010 0.02991 0.02051 0.0707 0.1550 0.9439
10.500 0.7175 0.03063 0.02119 0.0713 0.1484 0.9462
10.750 0.7361 0.03127 0.02195 0.0717 0.1418 0.9484
11.000 0.7515 0.03199 0.02269 0.0724 0.1355 0.9509
11.250 0.7675 0.03275 0.02349 0.0730 0.1301 0.9534
11.500 0.7859 0.03357 0.02441 0.0731 0.1243 0.9555
11.750 0.8032 0.03452 0.02535 0.0730 0.1194 0.9576
12.000 0.8220 0.03547 0.02645 0.0729 0.1142 0.9599
12.250 0.8385 0.03647 0.02753 0.0730 0.1094 0.9626
12.500 0.8539 0.03754 0.02857 0.0730 0.1056 0.9656
12.750 0.8702 0.03870 0.02995 0.0729 0.1011 0.9687
13.000 0.8864 0.03995 0.03130 0.0724 0.0970 0.9717
13.250 0.9017 0.04122 0.03257 0.0720 0.0937 0.9755
13.500 0.9156 0.04269 0.03424 0.0717 0.0901 0.9803
13.750 0.9282 0.04420 0.03590 0.0712 0.0865 0.9862
14.000 0.9395 0.04570 0.03747 0.0709 0.0838 0.9980
14.250 0.9436 0.04701 0.03875 0.0721 0.0817 1.0000
14.500 0.9435 0.04878 0.04076 0.0732 0.0791 1.0000
14.750 0.9453 0.05064 0.04276 0.0739 0.0768 1.0000
15.000 0.9478 0.05254 0.04474 0.0743 0.0746 1.0000
15.250 0.9515 0.05442 0.04664 0.0744 0.0728 1.0000
15.500 0.9532 0.05673 0.04903 0.0743 0.0709 1.0000
15.750 0.9488 0.05983 0.05239 0.0740 0.0690 1.0000
16.000 0.9447 0.06302 0.05576 0.0734 0.0672 1.0000
16.250 0.9413 0.06622 0.05908 0.0725 0.0656 1.0000
16.500 0.9400 0.06930 0.06224 0.0715 0.0642 1.0000
16.750 0.9435 0.07179 0.06470 0.0706 0.0627 1.0000
17.000 0.9281 0.07708 0.07025 0.0685 0.0616 1.0000
17.250 0.9062 0.08368 0.07713 0.0653 0.0606 1.0000
17.500 0.8778 0.09174 0.08545 0.0611 0.0598 1.0000
17.750 0.8278 0.10438 0.09842 0.0538 0.0596 1.0000
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