S1046 17% (Danny Howell) (s1046-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1046 17% (Danny Howell) (s1046-il) Reynolds number: 200,000 Max Cl/Cd: 55.02 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1046-il-200000.txt Download as CSV file: xf-s1046-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S1046 17% (Danny Howell)
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
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0395 0.08881 0.08308 -0.0218 1.0000 0.0390
-17.000 -1.0392 0.08569 0.07997 -0.0226 1.0000 0.0409
-16.750 -1.0424 0.08185 0.07613 -0.0242 1.0000 0.0428
-16.500 -1.0449 0.07810 0.07230 -0.0257 1.0000 0.0447
-16.250 -1.0486 0.07413 0.06818 -0.0272 1.0000 0.0469
-16.000 -1.0528 0.07060 0.06472 -0.0281 1.0000 0.0496
-15.750 -1.0575 0.06679 0.06087 -0.0295 1.0000 0.0522
-15.500 -1.0619 0.06300 0.05692 -0.0308 1.0000 0.0556
-15.250 -1.0702 0.05912 0.05311 -0.0318 1.0000 0.0590
-15.000 -1.0762 0.05541 0.04934 -0.0330 1.0000 0.0631
-14.750 -1.0825 0.05189 0.04577 -0.0337 1.0000 0.0676
-14.500 -1.0903 0.04833 0.04220 -0.0345 1.0000 0.0723
-14.250 -1.0947 0.04524 0.03902 -0.0350 1.0000 0.0780
-14.000 -1.1017 0.04205 0.03586 -0.0353 1.0000 0.0834
-13.750 -1.1041 0.03938 0.03311 -0.0354 1.0000 0.0900
-13.500 -1.1081 0.03670 0.03045 -0.0353 1.0000 0.0965
-13.250 -1.1092 0.03440 0.02809 -0.0349 1.0000 0.1035
-13.000 -1.1093 0.03229 0.02596 -0.0343 1.0000 0.1110
-12.750 -1.1093 0.03033 0.02399 -0.0335 1.0000 0.1182
-12.500 -1.1051 0.02876 0.02231 -0.0326 1.0000 0.1270
-12.250 -1.1050 0.02709 0.02071 -0.0312 1.0000 0.1346
-12.000 -1.1004 0.02579 0.01935 -0.0298 1.0000 0.1433
-11.750 -1.0961 0.02462 0.01816 -0.0280 1.0000 0.1522
-11.500 -1.0918 0.02356 0.01712 -0.0259 1.0000 0.1607
-11.250 -1.0846 0.02274 0.01622 -0.0238 1.0000 0.1702
-11.000 -1.0797 0.02195 0.01547 -0.0211 1.0000 0.1791
-10.750 -1.0736 0.02130 0.01482 -0.0182 1.0000 0.1885
-10.500 -1.0641 0.02079 0.01422 -0.0157 1.0000 0.1992
-10.250 -1.0535 0.02025 0.01372 -0.0134 1.0000 0.2099
-10.000 -1.0410 0.01976 0.01325 -0.0113 1.0000 0.2205
-9.750 -1.0269 0.01932 0.01277 -0.0093 1.0000 0.2312
-9.500 -1.0120 0.01893 0.01234 -0.0074 1.0000 0.2413
-9.250 -0.9964 0.01849 0.01194 -0.0056 1.0000 0.2505
-9.000 -0.9811 0.01814 0.01151 -0.0036 1.0000 0.2603
-8.750 -0.9658 0.01778 0.01120 -0.0017 1.0000 0.2693
-8.500 -0.9514 0.01744 0.01086 0.0005 1.0000 0.2784
-8.250 -0.9400 0.01721 0.01060 0.0031 1.0000 0.2875
-8.000 -0.9328 0.01696 0.01040 0.0063 1.0000 0.2950
-7.750 -0.9136 0.01680 0.01014 0.0070 0.9968 0.3053
-7.500 -0.8699 0.01647 0.00986 0.0034 0.9882 0.3176
-7.250 -0.8257 0.01616 0.00954 -0.0003 0.9802 0.3296
-7.000 -0.7837 0.01583 0.00919 -0.0034 0.9707 0.3415
-6.750 -0.7424 0.01555 0.00884 -0.0063 0.9610 0.3536
-6.500 -0.6997 0.01524 0.00854 -0.0094 0.9529 0.3650
-6.250 -0.6631 0.01495 0.00826 -0.0112 0.9402 0.3754
-6.000 -0.6288 0.01470 0.00795 -0.0125 0.9267 0.3864
-5.750 -0.5977 0.01450 0.00773 -0.0130 0.9126 0.3966
-5.500 -0.5697 0.01430 0.00752 -0.0129 0.8981 0.4060
-5.250 -0.5445 0.01419 0.00729 -0.0122 0.8835 0.4165
-5.000 -0.5191 0.01403 0.00716 -0.0114 0.8698 0.4255
-4.750 -0.4945 0.01390 0.00696 -0.0106 0.8568 0.4353
-4.500 -0.4701 0.01380 0.00683 -0.0097 0.8429 0.4455
-4.250 -0.4451 0.01368 0.00669 -0.0090 0.8300 0.4548
-4.000 -0.4203 0.01359 0.00653 -0.0082 0.8177 0.4656
-3.750 -0.3948 0.01350 0.00643 -0.0075 0.8066 0.4754
-3.500 -0.3693 0.01339 0.00631 -0.0069 0.7942 0.4857
-3.250 -0.3440 0.01334 0.00618 -0.0063 0.7822 0.4970
-3.000 -0.3178 0.01324 0.00611 -0.0057 0.7714 0.5068
-2.750 -0.2918 0.01316 0.00600 -0.0051 0.7601 0.5174
-2.500 -0.2660 0.01312 0.00591 -0.0046 0.7483 0.5291
-2.250 -0.2395 0.01305 0.00587 -0.0041 0.7375 0.5390
-2.000 -0.2131 0.01300 0.00579 -0.0036 0.7267 0.5499
-1.750 -0.1869 0.01297 0.00573 -0.0031 0.7148 0.5618
-1.500 -0.1602 0.01293 0.00572 -0.0026 0.7042 0.5719
-1.250 -0.1335 0.01290 0.00566 -0.0022 0.6935 0.5828
-1.000 -0.1071 0.01289 0.00563 -0.0017 0.6817 0.5946
-0.750 -0.0803 0.01288 0.00564 -0.0013 0.6711 0.6050
-0.500 -0.0534 0.01286 0.00561 -0.0008 0.6605 0.6158
-0.250 -0.0269 0.01286 0.00560 -0.0004 0.6488 0.6275
0.000 0.0000 0.01286 0.00562 0.0000 0.6381 0.6381
0.250 0.0269 0.01286 0.00560 0.0004 0.6275 0.6488
0.500 0.0534 0.01286 0.00561 0.0008 0.6158 0.6605
0.750 0.0803 0.01288 0.00564 0.0013 0.6050 0.6711
1.000 0.1071 0.01289 0.00563 0.0017 0.5946 0.6817
1.250 0.1335 0.01290 0.00566 0.0022 0.5827 0.6935
1.500 0.1602 0.01293 0.00572 0.0026 0.5719 0.7042
1.750 0.1869 0.01297 0.00573 0.0031 0.5618 0.7148
2.000 0.2131 0.01300 0.00579 0.0036 0.5499 0.7267
2.250 0.2395 0.01305 0.00588 0.0041 0.5391 0.7375
2.500 0.2660 0.01312 0.00591 0.0046 0.5291 0.7483
2.750 0.2918 0.01316 0.00600 0.0051 0.5174 0.7601
3.000 0.3178 0.01324 0.00611 0.0057 0.5068 0.7714
3.250 0.3439 0.01334 0.00618 0.0063 0.4970 0.7823
3.500 0.3693 0.01339 0.00631 0.0069 0.4856 0.7942
3.750 0.3948 0.01350 0.00643 0.0075 0.4754 0.8066
4.000 0.4203 0.01359 0.00653 0.0082 0.4656 0.8178
4.250 0.4451 0.01368 0.00669 0.0090 0.4548 0.8299
4.500 0.4701 0.01380 0.00682 0.0097 0.4454 0.8429
4.750 0.4946 0.01390 0.00696 0.0106 0.4353 0.8567
5.000 0.5191 0.01403 0.00716 0.0114 0.4255 0.8698
5.250 0.5445 0.01419 0.00729 0.0122 0.4166 0.8835
5.500 0.5697 0.01430 0.00752 0.0129 0.4061 0.8981
5.750 0.5977 0.01450 0.00774 0.0130 0.3967 0.9126
6.000 0.6289 0.01470 0.00795 0.0125 0.3865 0.9268
6.250 0.6631 0.01495 0.00826 0.0112 0.3754 0.9402
6.750 0.7425 0.01555 0.00883 0.0063 0.3535 0.9611
7.000 0.7838 0.01583 0.00919 0.0034 0.3414 0.9707
7.250 0.8257 0.01615 0.00955 0.0003 0.3296 0.9803
7.500 0.8700 0.01648 0.00986 -0.0034 0.3177 0.9883
7.750 0.9137 0.01680 0.01013 -0.0070 0.3053 0.9968
8.000 0.9326 0.01695 0.01039 -0.0062 0.2950 1.0000
8.250 0.9399 0.01720 0.01060 -0.0030 0.2875 1.0000
8.500 0.9514 0.01744 0.01086 -0.0005 0.2784 1.0000
8.750 0.9658 0.01778 0.01120 0.0017 0.2693 1.0000
9.000 0.9811 0.01814 0.01151 0.0036 0.2603 1.0000
9.250 0.9964 0.01849 0.01193 0.0056 0.2505 1.0000
9.500 1.0121 0.01893 0.01234 0.0074 0.2414 1.0000
9.750 1.0270 0.01932 0.01276 0.0093 0.2312 1.0000
10.000 1.0412 0.01976 0.01325 0.0113 0.2205 1.0000
10.250 1.0537 0.02025 0.01372 0.0134 0.2098 1.0000
10.500 1.0643 0.02079 0.01422 0.0157 0.1991 1.0000
10.750 1.0738 0.02130 0.01481 0.0182 0.1884 1.0000
11.000 1.0800 0.02195 0.01547 0.0210 0.1790 1.0000
11.250 1.0850 0.02274 0.01622 0.0237 0.1702 1.0000
11.500 1.0922 0.02355 0.01711 0.0258 0.1606 1.0000
11.750 1.0966 0.02462 0.01816 0.0279 0.1520 1.0000
12.000 1.1008 0.02579 0.01935 0.0297 0.1432 1.0000
12.250 1.1056 0.02708 0.02069 0.0311 0.1345 1.0000
12.500 1.1059 0.02875 0.02230 0.0325 0.1269 1.0000
12.750 1.1102 0.03030 0.02397 0.0334 0.1182 1.0000
13.000 1.1102 0.03228 0.02594 0.0342 0.1109 1.0000
13.250 1.1101 0.03437 0.02807 0.0347 0.1035 1.0000
13.500 1.1091 0.03669 0.03043 0.0351 0.0963 1.0000
13.750 1.1051 0.03936 0.03308 0.0352 0.0899 1.0000
14.000 1.1027 0.04203 0.03584 0.0352 0.0832 1.0000
14.250 1.0956 0.04524 0.03902 0.0348 0.0778 1.0000
14.500 1.0915 0.04831 0.04218 0.0344 0.0721 1.0000
14.750 1.0837 0.05186 0.04572 0.0336 0.0675 1.0000
15.000 1.0774 0.05541 0.04934 0.0328 0.0628 1.0000
15.250 1.0714 0.05911 0.05309 0.0316 0.0588 1.0000
15.500 1.0636 0.06294 0.05687 0.0307 0.0555 1.0000
15.750 1.0591 0.06674 0.06082 0.0293 0.0520 1.0000
16.000 1.0543 0.07057 0.06468 0.0280 0.0494 1.0000
16.250 1.0499 0.07415 0.06821 0.0270 0.0468 1.0000
16.500 1.0469 0.07799 0.07219 0.0255 0.0447 1.0000
16.750 1.0434 0.08192 0.07619 0.0239 0.0425 1.0000
17.000 1.0406 0.08567 0.07994 0.0224 0.0407 1.0000
17.250 1.0401 0.08898 0.08326 0.0214 0.0388 1.0000
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Polar data table (+)
Polar graphs
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