S1014 (s1014-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1014 (s1014-il) Reynolds number: 200,000 Max Cl/Cd: 33.7 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1014-il-200000.txt Download as CSV file: xf-s1014-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S1014
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8173 0.11507 0.11119 -0.0414 1.0000 0.0470
-17.500 -0.8765 0.09942 0.09532 -0.0510 1.0000 0.0462
-17.250 -0.9219 0.08804 0.08368 -0.0577 1.0000 0.0459
-17.000 -0.9563 0.07956 0.07495 -0.0621 1.0000 0.0458
-16.750 -0.9864 0.07255 0.06766 -0.0651 1.0000 0.0459
-16.500 -1.0102 0.06695 0.06180 -0.0667 1.0000 0.0461
-16.250 -1.0294 0.06236 0.05695 -0.0675 1.0000 0.0464
-16.000 -1.0472 0.05839 0.05270 -0.0677 1.0000 0.0468
-15.750 -1.0553 0.05464 0.04875 -0.0676 1.0000 0.0475
-15.500 -1.0439 0.05262 0.04676 -0.0679 1.0000 0.0487
-15.250 -1.0383 0.05061 0.04469 -0.0679 1.0000 0.0498
-15.000 -1.0360 0.04855 0.04251 -0.0677 1.0000 0.0510
-14.750 -1.0340 0.04641 0.04021 -0.0672 1.0000 0.0522
-14.500 -1.0352 0.04444 0.03802 -0.0664 1.0000 0.0538
-14.250 -1.0374 0.04262 0.03593 -0.0651 1.0000 0.0548
-14.000 -1.0145 0.04059 0.03390 -0.0662 0.9856 0.0570
-13.750 -0.9951 0.03925 0.03252 -0.0674 0.9772 0.0591
-13.500 -0.9789 0.03774 0.03083 -0.0682 0.9712 0.0616
-13.250 -0.9647 0.03626 0.02908 -0.0686 0.9659 0.0637
-13.000 -0.9390 0.03470 0.02753 -0.0696 0.9625 0.0668
-12.750 -0.9202 0.03372 0.02650 -0.0701 0.9585 0.0698
-12.500 -0.9028 0.03263 0.02522 -0.0701 0.9548 0.0728
-12.250 -0.8818 0.03143 0.02392 -0.0702 0.9513 0.0761
-12.000 -0.8624 0.03062 0.02314 -0.0701 0.9478 0.0794
-11.750 -0.8452 0.02984 0.02225 -0.0697 0.9446 0.0830
-11.500 -0.8252 0.02895 0.02121 -0.0695 0.9422 0.0869
-11.250 -0.8027 0.02817 0.02049 -0.0696 0.9402 0.0912
-11.000 -0.7843 0.02752 0.01977 -0.0692 0.9380 0.0956
-10.750 -0.7615 0.02674 0.01892 -0.0692 0.9362 0.1004
-10.500 -0.7417 0.02611 0.01833 -0.0689 0.9342 0.1054
-10.250 -0.7228 0.02559 0.01769 -0.0684 0.9322 0.1107
-10.000 -0.6994 0.02487 0.01704 -0.0684 0.9308 0.1166
-9.750 -0.6801 0.02437 0.01650 -0.0679 0.9291 0.1231
-9.500 -0.6586 0.02377 0.01592 -0.0676 0.9277 0.1300
-9.250 -0.6392 0.02331 0.01544 -0.0671 0.9263 0.1374
-9.000 -0.6194 0.02278 0.01494 -0.0665 0.9249 0.1457
-8.750 -0.6002 0.02236 0.01449 -0.0659 0.9232 0.1550
-8.500 -0.5816 0.02181 0.01405 -0.0653 0.9219 0.1651
-8.250 -0.5633 0.02135 0.01362 -0.0646 0.9206 0.1767
-8.000 -0.5457 0.02092 0.01323 -0.0638 0.9193 0.1902
-7.750 -0.5298 0.02048 0.01288 -0.0628 0.9180 0.2057
-7.500 -0.5164 0.02001 0.01253 -0.0613 0.9167 0.2240
-7.250 -0.5052 0.01955 0.01221 -0.0596 0.9153 0.2460
-7.000 -0.4965 0.01909 0.01190 -0.0573 0.9135 0.2733
-6.750 -0.4926 0.01861 0.01162 -0.0541 0.9116 0.3073
-6.500 -0.4942 0.01818 0.01141 -0.0501 0.9101 0.3476
-6.250 -0.5055 0.01798 0.01144 -0.0441 0.9085 0.3885
-6.000 -0.5384 0.01838 0.01195 -0.0337 0.9052 0.4079
-5.750 -0.5790 0.01893 0.01254 -0.0214 0.9024 0.4181
-5.500 -0.6157 0.01915 0.01286 -0.0096 0.9001 0.4378
-5.250 -0.6334 0.01880 0.01286 -0.0015 0.8981 0.4961
-5.000 -0.6288 0.01888 0.01369 0.0035 0.8971 0.6043
-4.750 -0.5837 0.02072 0.01579 0.0024 0.8966 0.6790
-4.500 -0.5725 0.02116 0.01613 0.0055 0.8949 0.7060
-4.250 -0.5456 0.02192 0.01679 0.0059 0.8936 0.7253
-4.000 -0.5583 0.02252 0.01737 0.0136 0.8917 0.7352
-3.750 -0.5635 0.02290 0.01769 0.0197 0.8896 0.7473
-3.500 -0.5431 0.02389 0.01867 0.0218 0.8876 0.7555
-3.250 -0.5267 0.02454 0.01927 0.0243 0.8852 0.7654
-3.000 -0.4968 0.02553 0.02022 0.0247 0.8832 0.7727
-2.750 -0.4673 0.02613 0.02075 0.0248 0.8807 0.7814
-2.500 -0.4111 0.02742 0.02201 0.0209 0.8790 0.7857
-2.250 -0.4150 0.02748 0.02202 0.0263 0.8750 0.7968
-2.000 -0.3919 0.02830 0.02284 0.0280 0.8712 0.8008
-1.750 -0.3882 0.02819 0.02268 0.0319 0.8668 0.8122
-1.500 -0.3266 0.02946 0.02394 0.0272 0.8648 0.8151
-1.250 -0.2380 0.03114 0.02560 0.0177 0.8641 0.8195
-1.000 -0.1857 0.03185 0.02627 0.0138 0.8623 0.8301
-0.750 -0.0855 0.03257 0.02697 0.0008 0.8625 0.8313
-0.500 -0.1571 0.03243 0.02685 0.0189 0.8505 0.8461
-0.250 -0.0743 0.03281 0.02722 0.0087 0.8494 0.8469
0.000 0.0001 0.03291 0.02732 0.0000 0.8481 0.8481
0.250 0.0745 0.03281 0.02722 -0.0087 0.8469 0.8494
0.500 0.1575 0.03242 0.02684 -0.0190 0.8461 0.8505
0.750 0.0853 0.03257 0.02698 -0.0008 0.8314 0.8626
1.000 0.1863 0.03183 0.02626 -0.0139 0.8301 0.8623
1.250 0.2405 0.03107 0.02553 -0.0181 0.8194 0.8640
1.500 0.3260 0.02950 0.02397 -0.0271 0.8152 0.8648
1.750 0.3880 0.02821 0.02270 -0.0319 0.8122 0.8669
2.000 0.3918 0.02829 0.02284 -0.0280 0.8008 0.8713
2.250 0.4145 0.02749 0.02204 -0.0263 0.7968 0.8750
2.500 0.4104 0.02745 0.02204 -0.0208 0.7858 0.8790
2.750 0.4669 0.02615 0.02077 -0.0248 0.7815 0.8807
3.000 0.4966 0.02552 0.02021 -0.0247 0.7727 0.8832
3.250 0.5265 0.02453 0.01926 -0.0243 0.7654 0.8852
3.500 0.5429 0.02390 0.01868 -0.0218 0.7557 0.8875
3.750 0.5631 0.02291 0.01771 -0.0196 0.7474 0.8896
4.000 0.5579 0.02251 0.01736 -0.0136 0.7351 0.8917
4.250 0.5456 0.02192 0.01679 -0.0060 0.7253 0.8936
4.500 0.5726 0.02114 0.01611 -0.0055 0.7054 0.8950
4.750 0.5832 0.02071 0.01578 -0.0023 0.6790 0.8965
5.000 0.6285 0.01888 0.01369 -0.0035 0.6048 0.8971
5.250 0.6333 0.01879 0.01285 0.0015 0.4965 0.8981
5.500 0.6157 0.01914 0.01285 0.0096 0.4382 0.9001
5.750 0.5792 0.01892 0.01254 0.0214 0.4185 0.9024
6.000 0.5386 0.01838 0.01195 0.0337 0.4080 0.9052
6.250 0.5054 0.01798 0.01144 0.0441 0.3882 0.9085
6.500 0.4945 0.01817 0.01141 0.0500 0.3478 0.9101
6.750 0.4926 0.01861 0.01161 0.0541 0.3070 0.9117
7.000 0.4966 0.01909 0.01190 0.0572 0.2731 0.9136
7.250 0.5053 0.01955 0.01221 0.0595 0.2458 0.9153
7.500 0.5165 0.02001 0.01253 0.0613 0.2238 0.9167
7.750 0.5300 0.02048 0.01287 0.0627 0.2056 0.9180
8.000 0.5460 0.02092 0.01323 0.0638 0.1903 0.9193
8.250 0.5636 0.02134 0.01362 0.0646 0.1767 0.9206
8.500 0.5819 0.02181 0.01404 0.0653 0.1650 0.9219
8.750 0.6005 0.02235 0.01448 0.0659 0.1550 0.9233
9.000 0.6198 0.02277 0.01494 0.0664 0.1457 0.9250
9.250 0.6396 0.02330 0.01543 0.0670 0.1374 0.9264
9.500 0.6590 0.02377 0.01591 0.0675 0.1299 0.9277
9.750 0.6805 0.02437 0.01649 0.0678 0.1229 0.9291
10.000 0.7000 0.02486 0.01703 0.0683 0.1167 0.9308
10.250 0.7229 0.02557 0.01768 0.0684 0.1106 0.9323
10.500 0.7419 0.02610 0.01832 0.0689 0.1053 0.9343
10.750 0.7622 0.02674 0.01892 0.0691 0.1003 0.9362
11.000 0.7844 0.02751 0.01976 0.0692 0.0954 0.9381
11.250 0.8030 0.02815 0.02047 0.0696 0.0911 0.9403
11.500 0.8265 0.02896 0.02121 0.0693 0.0868 0.9422
11.750 0.8456 0.02983 0.02224 0.0696 0.0830 0.9447
12.000 0.8630 0.03062 0.02314 0.0700 0.0793 0.9479
12.250 0.8824 0.03142 0.02390 0.0701 0.0760 0.9515
12.500 0.9033 0.03262 0.02522 0.0700 0.0727 0.9549
12.750 0.9206 0.03371 0.02649 0.0700 0.0696 0.9587
13.000 0.9401 0.03470 0.02753 0.0695 0.0668 0.9626
13.250 0.9656 0.03624 0.02906 0.0685 0.0637 0.9661
13.500 0.9792 0.03771 0.03081 0.0681 0.0614 0.9715
13.750 0.9964 0.03925 0.03252 0.0672 0.0591 0.9775
14.000 1.0160 0.04057 0.03388 0.0660 0.0570 0.9861
14.250 1.0380 0.04262 0.03593 0.0650 0.0548 1.0000
14.500 1.0358 0.04444 0.03802 0.0663 0.0537 1.0000
14.750 1.0357 0.04647 0.04026 0.0670 0.0524 1.0000
15.000 1.0373 0.04852 0.04248 0.0675 0.0510 1.0000
15.250 1.0395 0.05062 0.04470 0.0677 0.0498 1.0000
15.500 1.0459 0.05253 0.04666 0.0677 0.0487 1.0000
15.750 1.0570 0.05463 0.04874 0.0674 0.0475 1.0000
16.000 1.0490 0.05833 0.05264 0.0675 0.0468 1.0000
16.250 1.0306 0.06238 0.05697 0.0674 0.0464 1.0000
16.500 1.0106 0.06706 0.06192 0.0665 0.0461 1.0000
16.750 0.9873 0.07256 0.06768 0.0649 0.0458 1.0000
17.000 0.9590 0.07935 0.07473 0.0620 0.0457 1.0000
17.250 0.9220 0.08821 0.08386 0.0574 0.0458 1.0000
17.500 0.8790 0.09921 0.09511 0.0509 0.0462 1.0000
17.750 0.8136 0.11615 0.11229 0.0404 0.0470 1.0000
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