S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 200,000 Max Cl/Cd: 45.3 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9026-il-200000-n5.txt Download as CSV file: xf-s9026-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9026 (9.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8923 0.09710 0.09331 0.0025 1.0000 0.0186
-13.750 -0.9447 0.08097 0.07700 -0.0082 1.0000 0.0178
-13.500 -0.9836 0.06893 0.06472 -0.0168 1.0000 0.0172
-13.250 -1.0044 0.06132 0.05691 -0.0223 1.0000 0.0172
-13.000 -1.0220 0.05506 0.05044 -0.0266 1.0000 0.0173
-12.750 -1.0358 0.05012 0.04529 -0.0294 1.0000 0.0174
-12.500 -1.0458 0.04634 0.04131 -0.0307 1.0000 0.0178
-12.250 -1.0554 0.04301 0.03776 -0.0309 1.0000 0.0181
-12.000 -1.0610 0.04048 0.03502 -0.0299 1.0000 0.0186
-11.750 -1.0652 0.03823 0.03253 -0.0281 1.0000 0.0191
-11.500 -1.0659 0.03627 0.03033 -0.0258 1.0000 0.0195
-11.250 -1.0604 0.03448 0.02825 -0.0240 1.0000 0.0200
-11.000 -1.0543 0.03246 0.02612 -0.0224 1.0000 0.0208
-10.750 -1.0425 0.03113 0.02471 -0.0211 1.0000 0.0217
-10.500 -1.0279 0.03002 0.02349 -0.0200 1.0000 0.0227
-10.250 -1.0128 0.02874 0.02205 -0.0188 1.0000 0.0237
-10.000 -0.9965 0.02744 0.02057 -0.0176 1.0000 0.0247
-9.750 -0.9788 0.02628 0.01921 -0.0165 1.0000 0.0258
-9.500 -0.9609 0.02507 0.01784 -0.0154 1.0000 0.0270
-9.250 -0.9437 0.02382 0.01651 -0.0142 1.0000 0.0283
-9.000 -0.9243 0.02286 0.01547 -0.0133 1.0000 0.0296
-8.750 -0.9042 0.02195 0.01445 -0.0123 1.0000 0.0311
-8.500 -0.8835 0.02108 0.01346 -0.0113 1.0000 0.0329
-8.250 -0.8617 0.02036 0.01260 -0.0104 1.0000 0.0348
-8.000 -0.8421 0.01938 0.01162 -0.0094 1.0000 0.0377
-7.750 -0.8202 0.01869 0.01085 -0.0086 1.0000 0.0408
-7.500 -0.7979 0.01804 0.01008 -0.0077 1.0000 0.0441
-7.250 -0.7765 0.01728 0.00931 -0.0067 1.0000 0.0482
-7.000 -0.7538 0.01672 0.00870 -0.0059 1.0000 0.0534
-6.750 -0.7312 0.01614 0.00810 -0.0051 1.0000 0.0595
-6.500 -0.7081 0.01566 0.00757 -0.0043 1.0000 0.0668
-6.250 -0.6854 0.01514 0.00706 -0.0034 1.0000 0.0744
-6.000 -0.6623 0.01470 0.00661 -0.0026 1.0000 0.0834
-5.500 -0.6164 0.01384 0.00579 -0.0009 1.0000 0.1077
-5.250 -0.5937 0.01342 0.00541 0.0000 1.0000 0.1227
-5.000 -0.5710 0.01301 0.00507 0.0009 1.0000 0.1389
-4.750 -0.5482 0.01264 0.00476 0.0018 1.0000 0.1559
-4.500 -0.5254 0.01229 0.00447 0.0027 1.0000 0.1754
-4.250 -0.5028 0.01195 0.00419 0.0036 1.0000 0.1973
-4.000 -0.4801 0.01164 0.00396 0.0046 1.0000 0.2202
-3.750 -0.4576 0.01134 0.00375 0.0055 1.0000 0.2442
-3.500 -0.4354 0.01104 0.00357 0.0065 1.0000 0.2720
-3.250 -0.4136 0.01076 0.00341 0.0076 1.0000 0.3039
-3.000 -0.3841 0.01047 0.00328 0.0070 0.9963 0.3415
-2.750 -0.3474 0.01019 0.00316 0.0050 0.9882 0.3830
-2.500 -0.3107 0.00994 0.00305 0.0030 0.9797 0.4236
-2.250 -0.2744 0.00968 0.00295 0.0012 0.9699 0.4652
-2.000 -0.2408 0.00943 0.00287 0.0001 0.9572 0.5067
-1.750 -0.2074 0.00919 0.00280 -0.0009 0.9440 0.5500
-1.500 -0.1742 0.00897 0.00275 -0.0018 0.9298 0.5926
-1.250 -0.1409 0.00879 0.00270 -0.0025 0.9135 0.6320
-1.000 -0.1094 0.00864 0.00266 -0.0028 0.8938 0.6678
-0.750 -0.0799 0.00852 0.00263 -0.0026 0.8711 0.7025
-0.500 -0.0522 0.00843 0.00261 -0.0020 0.8472 0.7361
-0.250 -0.0258 0.00838 0.00259 -0.0010 0.8223 0.7673
0.000 0.0000 0.00837 0.00259 0.0000 0.7958 0.7958
0.250 0.0258 0.00838 0.00259 0.0010 0.7673 0.8222
0.500 0.0522 0.00843 0.00261 0.0020 0.7360 0.8471
0.750 0.0799 0.00852 0.00263 0.0026 0.7025 0.8711
1.000 0.1094 0.00864 0.00266 0.0028 0.6678 0.8938
1.250 0.1409 0.00879 0.00270 0.0025 0.6320 0.9134
1.500 0.1742 0.00897 0.00275 0.0018 0.5928 0.9298
1.750 0.2075 0.00919 0.00280 0.0009 0.5502 0.9440
2.000 0.2409 0.00943 0.00287 -0.0001 0.5066 0.9572
2.250 0.2744 0.00968 0.00296 -0.0012 0.4651 0.9699
2.500 0.3108 0.00994 0.00305 -0.0030 0.4237 0.9796
2.750 0.3474 0.01020 0.00316 -0.0050 0.3829 0.9881
3.000 0.3841 0.01047 0.00328 -0.0070 0.3416 0.9962
3.250 0.4137 0.01076 0.00341 -0.0076 0.3037 1.0000
3.500 0.4356 0.01104 0.00357 -0.0066 0.2720 1.0000
3.750 0.4578 0.01134 0.00375 -0.0056 0.2441 1.0000
4.000 0.4802 0.01164 0.00396 -0.0046 0.2202 1.0000
4.250 0.5029 0.01195 0.00420 -0.0037 0.1972 1.0000
4.500 0.5255 0.01229 0.00447 -0.0027 0.1755 1.0000
4.750 0.5483 0.01264 0.00476 -0.0018 0.1557 1.0000
5.000 0.5712 0.01301 0.00507 -0.0009 0.1389 1.0000
5.250 0.5938 0.01342 0.00541 0.0000 0.1226 1.0000
5.500 0.6165 0.01384 0.00579 0.0009 0.1076 1.0000
6.000 0.6624 0.01470 0.00661 0.0026 0.0835 1.0000
6.250 0.6855 0.01514 0.00706 0.0034 0.0744 1.0000
6.500 0.7082 0.01566 0.00757 0.0043 0.0668 1.0000
6.750 0.7312 0.01614 0.00811 0.0051 0.0596 1.0000
7.000 0.7538 0.01672 0.00870 0.0059 0.0534 1.0000
7.250 0.7764 0.01729 0.00932 0.0067 0.0481 1.0000
7.500 0.7978 0.01804 0.01009 0.0077 0.0440 1.0000
7.750 0.8201 0.01869 0.01085 0.0086 0.0408 1.0000
8.000 0.8420 0.01937 0.01161 0.0094 0.0376 1.0000
8.250 0.8617 0.02034 0.01258 0.0105 0.0348 1.0000
8.500 0.8833 0.02108 0.01347 0.0114 0.0329 1.0000
8.750 0.9039 0.02195 0.01446 0.0123 0.0311 1.0000
9.000 0.9241 0.02285 0.01546 0.0133 0.0296 1.0000
9.250 0.9435 0.02381 0.01650 0.0143 0.0283 1.0000
9.500 0.9606 0.02507 0.01784 0.0154 0.0269 1.0000
9.750 0.9784 0.02629 0.01923 0.0166 0.0259 1.0000
10.000 0.9962 0.02744 0.02057 0.0176 0.0247 1.0000
10.250 1.0124 0.02875 0.02206 0.0188 0.0237 1.0000
10.500 1.0277 0.03001 0.02347 0.0200 0.0227 1.0000
10.750 1.0421 0.03115 0.02473 0.0212 0.0217 1.0000
11.000 1.0542 0.03241 0.02607 0.0224 0.0208 1.0000
11.250 1.0600 0.03449 0.02826 0.0241 0.0200 1.0000
11.500 1.0656 0.03625 0.03032 0.0259 0.0195 1.0000
11.750 1.0649 0.03821 0.03251 0.0282 0.0190 1.0000
12.000 1.0610 0.04046 0.03500 0.0300 0.0186 1.0000
12.250 1.0541 0.04319 0.03795 0.0309 0.0182 1.0000
12.500 1.0453 0.04640 0.04138 0.0307 0.0179 1.0000
12.750 1.0348 0.05029 0.04547 0.0293 0.0175 1.0000
13.000 1.0210 0.05526 0.05064 0.0265 0.0174 1.0000
13.250 1.0039 0.06146 0.05705 0.0222 0.0173 1.0000
13.500 0.9775 0.07017 0.06599 0.0159 0.0175 1.0000
13.750 0.9455 0.08089 0.07693 0.0082 0.0178 1.0000
14.000 0.8925 0.09718 0.09338 -0.0026 0.0186 1.0000
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Polar data table (+)
Polar graphs
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