S1048 14% (Danny Howell) (s1048-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1048 14% (Danny Howell) (s1048-il) Reynolds number: 100,000 Max Cl/Cd: 41.61 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1048-il-100000-n5.txt Download as CSV file: xf-s1048-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1048 14% (Danny Howell)
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8295 0.12513 0.11958 0.0030 1.0000 0.0201
-16.000 -0.8463 0.11674 0.11104 -0.0018 1.0000 0.0201
-15.750 -0.8621 0.10892 0.10304 -0.0064 1.0000 0.0201
-15.500 -0.8734 0.10248 0.09647 -0.0099 1.0000 0.0203
-15.250 -0.8800 0.09737 0.09131 -0.0125 1.0000 0.0209
-15.000 -0.8883 0.09188 0.08570 -0.0153 1.0000 0.0211
-14.750 -0.8953 0.08683 0.08053 -0.0178 1.0000 0.0214
-14.500 -0.9022 0.08201 0.07562 -0.0203 1.0000 0.0220
-14.250 -0.9083 0.07744 0.07091 -0.0224 1.0000 0.0225
-14.000 -0.9138 0.07312 0.06646 -0.0243 1.0000 0.0231
-13.750 -0.9187 0.06902 0.06221 -0.0259 1.0000 0.0239
-13.500 -0.9211 0.06536 0.05840 -0.0270 1.0000 0.0246
-13.250 -0.9231 0.06185 0.05470 -0.0279 1.0000 0.0255
-13.000 -0.9224 0.05880 0.05149 -0.0284 1.0000 0.0262
-12.750 -0.9227 0.05577 0.04838 -0.0288 1.0000 0.0270
-12.500 -0.9263 0.05246 0.04503 -0.0294 1.0000 0.0281
-12.250 -0.9278 0.04948 0.04197 -0.0299 1.0000 0.0291
-12.000 -0.9290 0.04659 0.03899 -0.0303 1.0000 0.0308
-11.750 -0.9287 0.04398 0.03624 -0.0305 1.0000 0.0330
-11.500 -0.9272 0.04159 0.03368 -0.0302 1.0000 0.0349
-11.250 -0.9318 0.03884 0.03090 -0.0299 1.0000 0.0369
-11.000 -0.9328 0.03656 0.02855 -0.0292 1.0000 0.0396
-10.750 -0.9316 0.03461 0.02648 -0.0281 1.0000 0.0429
-10.500 -0.9333 0.03266 0.02449 -0.0265 1.0000 0.0467
-10.250 -0.9333 0.03100 0.02278 -0.0244 1.0000 0.0518
-10.000 -0.9333 0.02949 0.02125 -0.0218 1.0000 0.0575
-9.750 -0.9298 0.02815 0.01986 -0.0192 1.0000 0.0664
-9.500 -0.9242 0.02677 0.01853 -0.0170 1.0000 0.0783
-9.250 -0.9162 0.02550 0.01731 -0.0149 1.0000 0.0931
-9.000 -0.9063 0.02433 0.01621 -0.0130 1.0000 0.1114
-8.750 -0.8937 0.02332 0.01522 -0.0113 1.0000 0.1327
-8.500 -0.8806 0.02238 0.01435 -0.0096 1.0000 0.1561
-8.250 -0.8663 0.02154 0.01360 -0.0080 1.0000 0.1811
-8.000 -0.8507 0.02082 0.01294 -0.0064 1.0000 0.2062
-7.750 -0.8338 0.02022 0.01234 -0.0049 1.0000 0.2300
-7.500 -0.8165 0.01966 0.01182 -0.0034 1.0000 0.2499
-7.250 -0.7983 0.01919 0.01131 -0.0020 1.0000 0.2693
-7.000 -0.7797 0.01876 0.01085 -0.0005 1.0000 0.2881
-6.750 -0.7614 0.01837 0.01046 0.0010 1.0000 0.3058
-6.500 -0.7428 0.01801 0.01010 0.0025 1.0000 0.3223
-6.250 -0.7240 0.01769 0.00975 0.0039 1.0000 0.3382
-6.000 -0.7055 0.01739 0.00942 0.0054 1.0000 0.3533
-5.750 -0.6874 0.01712 0.00913 0.0070 1.0000 0.3676
-5.500 -0.6701 0.01688 0.00888 0.0087 1.0000 0.3815
-5.250 -0.6377 0.01666 0.00862 0.0073 0.9917 0.3978
-5.000 -0.5993 0.01644 0.00835 0.0049 0.9786 0.4146
-4.750 -0.5610 0.01623 0.00807 0.0026 0.9655 0.4308
-4.500 -0.5227 0.01602 0.00782 0.0004 0.9527 0.4462
-4.250 -0.4853 0.01582 0.00759 -0.0016 0.9391 0.4613
-4.000 -0.4489 0.01564 0.00735 -0.0033 0.9248 0.4757
-3.750 -0.4140 0.01547 0.00715 -0.0046 0.9097 0.4897
-3.500 -0.3810 0.01532 0.00697 -0.0054 0.8937 0.5032
-3.250 -0.3498 0.01519 0.00679 -0.0059 0.8773 0.5164
-3.000 -0.3201 0.01507 0.00663 -0.0060 0.8608 0.5293
-2.750 -0.2918 0.01497 0.00649 -0.0059 0.8443 0.5422
-2.500 -0.2643 0.01488 0.00635 -0.0055 0.8282 0.5551
-2.250 -0.2374 0.01481 0.00622 -0.0051 0.8124 0.5681
-2.000 -0.2108 0.01475 0.00612 -0.0045 0.7970 0.5809
-1.750 -0.1841 0.01470 0.00605 -0.0040 0.7820 0.5933
-1.500 -0.1576 0.01465 0.00598 -0.0035 0.7673 0.6058
-1.250 -0.1312 0.01461 0.00593 -0.0029 0.7528 0.6186
-1.000 -0.1048 0.01458 0.00587 -0.0023 0.7387 0.6315
-0.750 -0.0786 0.01456 0.00583 -0.0018 0.7248 0.6447
-0.500 -0.0524 0.01455 0.00579 -0.0012 0.7112 0.6580
-0.250 -0.0262 0.01454 0.00577 -0.0006 0.6978 0.6716
0.000 0.0000 0.01454 0.00576 0.0000 0.6847 0.6846
0.250 0.0262 0.01454 0.00577 0.0006 0.6716 0.6978
0.500 0.0524 0.01455 0.00579 0.0012 0.6580 0.7112
0.750 0.0786 0.01456 0.00583 0.0018 0.6447 0.7248
1.000 0.1048 0.01458 0.00587 0.0023 0.6315 0.7387
1.250 0.1312 0.01461 0.00593 0.0029 0.6186 0.7529
1.500 0.1576 0.01465 0.00598 0.0035 0.6058 0.7673
1.750 0.1841 0.01470 0.00605 0.0040 0.5932 0.7820
2.000 0.2108 0.01475 0.00612 0.0045 0.5809 0.7971
2.250 0.2374 0.01481 0.00622 0.0051 0.5681 0.8125
2.500 0.2643 0.01488 0.00635 0.0055 0.5551 0.8283
2.750 0.2918 0.01497 0.00649 0.0059 0.5422 0.8443
3.000 0.3201 0.01507 0.00663 0.0060 0.5293 0.8608
3.250 0.3498 0.01519 0.00679 0.0059 0.5164 0.8773
3.500 0.3810 0.01532 0.00697 0.0054 0.5032 0.8937
3.750 0.4140 0.01547 0.00715 0.0046 0.4897 0.9097
4.000 0.4488 0.01564 0.00735 0.0033 0.4756 0.9248
4.250 0.4853 0.01582 0.00759 0.0016 0.4612 0.9392
4.500 0.5227 0.01602 0.00782 -0.0004 0.4463 0.9526
4.750 0.5610 0.01623 0.00807 -0.0026 0.4307 0.9655
5.000 0.5993 0.01644 0.00835 -0.0049 0.4147 0.9786
5.250 0.6377 0.01665 0.00862 -0.0073 0.3978 0.9917
5.500 0.6701 0.01688 0.00888 -0.0087 0.3814 1.0000
5.750 0.6874 0.01712 0.00913 -0.0070 0.3676 1.0000
6.000 0.7055 0.01739 0.00942 -0.0054 0.3532 1.0000
6.250 0.7241 0.01769 0.00976 -0.0039 0.3382 1.0000
6.500 0.7428 0.01801 0.01010 -0.0025 0.3223 1.0000
6.750 0.7614 0.01837 0.01046 -0.0010 0.3056 1.0000
7.000 0.7798 0.01876 0.01085 0.0005 0.2881 1.0000
7.250 0.7984 0.01919 0.01131 0.0020 0.2694 1.0000
7.500 0.8166 0.01966 0.01182 0.0034 0.2499 1.0000
7.750 0.8338 0.02022 0.01234 0.0049 0.2300 1.0000
8.000 0.8507 0.02082 0.01294 0.0064 0.2062 1.0000
8.250 0.8662 0.02154 0.01360 0.0080 0.1811 1.0000
8.500 0.8805 0.02238 0.01435 0.0096 0.1560 1.0000
8.750 0.8936 0.02332 0.01522 0.0113 0.1325 1.0000
9.000 0.9063 0.02433 0.01621 0.0130 0.1112 1.0000
9.250 0.9162 0.02550 0.01730 0.0149 0.0932 1.0000
9.500 0.9242 0.02677 0.01853 0.0170 0.0784 1.0000
9.750 0.9297 0.02815 0.01986 0.0193 0.0665 1.0000
10.000 0.9332 0.02950 0.02125 0.0218 0.0574 1.0000
10.250 0.9333 0.03100 0.02279 0.0244 0.0519 1.0000
10.500 0.9334 0.03266 0.02450 0.0265 0.0468 1.0000
10.750 0.9318 0.03462 0.02648 0.0281 0.0433 1.0000
11.000 0.9331 0.03656 0.02855 0.0292 0.0396 1.0000
11.250 0.9324 0.03881 0.03087 0.0299 0.0370 1.0000
11.500 0.9275 0.04159 0.03367 0.0302 0.0348 1.0000
11.750 0.9296 0.04394 0.03621 0.0303 0.0325 1.0000
12.000 0.9299 0.04654 0.03893 0.0303 0.0309 1.0000
12.250 0.9282 0.04947 0.04195 0.0298 0.0289 1.0000
12.500 0.9267 0.05247 0.04503 0.0293 0.0280 1.0000
12.750 0.9246 0.05561 0.04823 0.0287 0.0271 1.0000
13.000 0.9231 0.05878 0.05148 0.0284 0.0261 1.0000
13.250 0.9237 0.06186 0.05473 0.0278 0.0254 1.0000
13.500 0.9224 0.06528 0.05831 0.0270 0.0246 1.0000
13.750 0.9189 0.06910 0.06229 0.0257 0.0237 1.0000
14.000 0.9147 0.07310 0.06643 0.0242 0.0230 1.0000
14.250 0.9089 0.07745 0.07091 0.0222 0.0223 1.0000
14.500 0.9033 0.08196 0.07556 0.0202 0.0219 1.0000
14.750 0.8966 0.08675 0.08044 0.0177 0.0213 1.0000
15.000 0.8893 0.09188 0.08572 0.0152 0.0212 1.0000
15.250 0.8819 0.09714 0.09106 0.0125 0.0207 1.0000
15.500 0.8738 0.10264 0.09665 0.0097 0.0204 1.0000
15.750 0.8630 0.10896 0.10308 0.0062 0.0201 1.0000
16.000 0.8472 0.11681 0.11111 0.0017 0.0201 1.0000
16.250 0.8293 0.12549 0.11995 -0.0034 0.0201 1.0000
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Polar data table (+)
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