ULTIMATE (ultimate-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: ULTIMATE (ultimate-il) Reynolds number: 100,000 Max Cl/Cd: 36.13 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ultimate-il-100000-n5.txt Download as CSV file: xf-ultimate-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ULTIMATE
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7677 0.11815 0.11315 0.0041 1.0000 0.0278
-13.500 -0.8600 0.09141 0.08607 -0.0144 1.0000 0.0254
-13.250 -0.8956 0.08157 0.07596 -0.0210 1.0000 0.0251
-13.000 -0.9202 0.07473 0.06887 -0.0248 1.0000 0.0250
-12.750 -0.9407 0.06915 0.06303 -0.0270 1.0000 0.0249
-12.500 -0.9562 0.06463 0.05829 -0.0280 1.0000 0.0250
-12.250 -0.9694 0.06066 0.05408 -0.0281 1.0000 0.0251
-12.000 -0.9786 0.05735 0.05057 -0.0275 1.0000 0.0254
-11.750 -0.9853 0.05450 0.04752 -0.0263 1.0000 0.0257
-11.500 -0.9901 0.05195 0.04474 -0.0246 1.0000 0.0262
-11.250 -0.9924 0.04968 0.04228 -0.0226 1.0000 0.0269
-11.000 -0.9935 0.04752 0.03989 -0.0201 1.0000 0.0277
-10.750 -0.9931 0.04531 0.03741 -0.0174 1.0000 0.0284
-10.500 -0.9885 0.04307 0.03486 -0.0151 1.0000 0.0293
-10.250 -0.9788 0.04081 0.03227 -0.0132 1.0000 0.0300
-10.000 -0.9655 0.03871 0.02985 -0.0117 1.0000 0.0307
-9.750 -0.9489 0.03650 0.02749 -0.0106 1.0000 0.0316
-9.500 -0.9326 0.03474 0.02569 -0.0096 1.0000 0.0328
-9.250 -0.9170 0.03336 0.02422 -0.0083 1.0000 0.0346
-9.000 -0.9002 0.03203 0.02274 -0.0070 1.0000 0.0368
-8.750 -0.8821 0.03069 0.02122 -0.0058 1.0000 0.0386
-8.500 -0.8658 0.02921 0.01968 -0.0043 1.0000 0.0402
-8.250 -0.8520 0.02789 0.01836 -0.0025 1.0000 0.0424
-8.000 -0.8366 0.02684 0.01723 -0.0008 1.0000 0.0457
-7.750 -0.8206 0.02586 0.01611 0.0009 1.0000 0.0490
-7.500 -0.8080 0.02467 0.01491 0.0032 1.0000 0.0522
-7.250 -0.7931 0.02372 0.01389 0.0051 1.0000 0.0570
-7.000 -0.7786 0.02276 0.01289 0.0072 1.0000 0.0639
-6.750 -0.7635 0.02187 0.01195 0.0092 1.0000 0.0732
-6.500 -0.7506 0.02083 0.01104 0.0116 1.0000 0.0900
-6.250 -0.7393 0.01974 0.01023 0.0141 1.0000 0.1298
-6.000 -0.7288 0.01871 0.00957 0.0169 1.0000 0.1902
-5.750 -0.7182 0.01789 0.00909 0.0197 1.0000 0.2528
-5.500 -0.7057 0.01733 0.00876 0.0223 1.0000 0.3073
-5.250 -0.6917 0.01693 0.00847 0.0248 1.0000 0.3519
-5.000 -0.6771 0.01660 0.00823 0.0272 1.0000 0.3920
-4.750 -0.6637 0.01625 0.00805 0.0298 1.0000 0.4355
-4.500 -0.6493 0.01595 0.00790 0.0323 1.0000 0.4747
-4.250 -0.6315 0.01571 0.00773 0.0341 0.9996 0.5052
-4.000 -0.5950 0.01551 0.00754 0.0321 0.9937 0.5335
-3.750 -0.5585 0.01532 0.00736 0.0302 0.9869 0.5617
-3.500 -0.5219 0.01516 0.00721 0.0283 0.9799 0.5903
-3.250 -0.4835 0.01503 0.00711 0.0260 0.9735 0.6195
-3.000 -0.4488 0.01491 0.00702 0.0247 0.9651 0.6475
-2.750 -0.4128 0.01481 0.00692 0.0231 0.9574 0.6746
-2.500 -0.3793 0.01471 0.00682 0.0220 0.9482 0.6999
-2.250 -0.3462 0.01462 0.00675 0.0211 0.9385 0.7221
-2.000 -0.3115 0.01453 0.00663 0.0199 0.9301 0.7437
-1.750 -0.2786 0.01445 0.00656 0.0191 0.9198 0.7631
-1.500 -0.2448 0.01438 0.00650 0.0182 0.9098 0.7813
-1.250 -0.2092 0.01431 0.00641 0.0169 0.9010 0.7986
-1.000 -0.1764 0.01426 0.00637 0.0162 0.8897 0.8153
-0.750 -0.1434 0.01423 0.00633 0.0155 0.8784 0.8312
-0.500 -0.1099 0.01420 0.00628 0.0147 0.8671 0.8465
-0.250 -0.0762 0.01417 0.00624 0.0138 0.8554 0.8609
0.000 -0.0424 0.01416 0.00623 0.0129 0.8422 0.8747
0.250 -0.0082 0.01416 0.00624 0.0118 0.8279 0.8876
0.500 0.0266 0.01418 0.00626 0.0105 0.8131 0.9001
0.750 0.0645 0.01421 0.00631 0.0087 0.7976 0.9103
1.000 0.1036 0.01425 0.00636 0.0066 0.7818 0.9192
1.250 0.1407 0.01429 0.00640 0.0048 0.7656 0.9289
1.500 0.1812 0.01437 0.00649 0.0024 0.7485 0.9358
1.750 0.2180 0.01445 0.00658 0.0007 0.7310 0.9446
2.000 0.2558 0.01457 0.00671 -0.0012 0.7134 0.9533
2.250 0.2941 0.01470 0.00685 -0.0032 0.6958 0.9632
2.500 0.3312 0.01486 0.00700 -0.0051 0.6778 0.9750
3.000 0.4036 0.01517 0.00730 -0.0088 0.6355 0.9952
3.250 0.4376 0.01525 0.00737 -0.0103 0.6148 1.0000
3.500 0.4599 0.01528 0.00741 -0.0095 0.5973 1.0000
3.750 0.4825 0.01534 0.00749 -0.0087 0.5800 1.0000
4.000 0.5050 0.01542 0.00761 -0.0078 0.5618 1.0000
4.250 0.5267 0.01553 0.00768 -0.0067 0.5358 1.0000
4.500 0.5476 0.01567 0.00774 -0.0055 0.4946 1.0000
4.750 0.5679 0.01593 0.00779 -0.0042 0.4417 1.0000
5.000 0.5885 0.01629 0.00796 -0.0030 0.3826 1.0000
5.250 0.6081 0.01686 0.00821 -0.0019 0.3040 1.0000
5.500 0.6249 0.01798 0.00876 -0.0007 0.2018 1.0000
6.000 0.6575 0.02058 0.01050 0.0020 0.0751 1.0000
6.250 0.6753 0.02156 0.01143 0.0034 0.0634 1.0000
6.500 0.6936 0.02242 0.01237 0.0047 0.0562 1.0000
6.750 0.7097 0.02351 0.01347 0.0064 0.0521 1.0000
7.000 0.7274 0.02440 0.01449 0.0080 0.0485 1.0000
7.250 0.7441 0.02537 0.01549 0.0095 0.0447 1.0000
7.500 0.7583 0.02673 0.01679 0.0113 0.0421 1.0000
7.750 0.7763 0.02782 0.01803 0.0128 0.0404 1.0000
8.000 0.7945 0.02901 0.01933 0.0143 0.0384 1.0000
8.250 0.8123 0.03019 0.02058 0.0156 0.0362 1.0000
8.500 0.8295 0.03148 0.02187 0.0168 0.0342 1.0000
8.750 0.8477 0.03333 0.02373 0.0180 0.0329 1.0000
9.000 0.8664 0.03498 0.02562 0.0193 0.0320 1.0000
9.250 0.8837 0.03687 0.02780 0.0206 0.0311 1.0000
9.500 0.8987 0.03883 0.03003 0.0222 0.0301 1.0000
9.750 0.9115 0.04072 0.03215 0.0238 0.0289 1.0000
10.000 0.9227 0.04247 0.03406 0.0254 0.0277 1.0000
10.250 0.9323 0.04433 0.03606 0.0271 0.0268 1.0000
10.500 0.9397 0.04664 0.03852 0.0288 0.0262 1.0000
10.750 0.9433 0.04957 0.04162 0.0307 0.0258 1.0000
11.000 0.9388 0.05231 0.04470 0.0336 0.0256 1.0000
11.250 0.9285 0.05505 0.04775 0.0368 0.0255 1.0000
11.500 0.9137 0.05793 0.05089 0.0398 0.0254 1.0000
11.750 0.8980 0.06126 0.05446 0.0416 0.0253 1.0000
12.000 0.8809 0.06509 0.05852 0.0424 0.0253 1.0000
12.250 0.8626 0.06950 0.06314 0.0419 0.0253 1.0000
12.500 0.8425 0.07466 0.06850 0.0402 0.0254 1.0000
12.750 0.8219 0.08055 0.07453 0.0375 0.0254 1.0000
13.000 0.8008 0.08723 0.08136 0.0337 0.0256 1.0000
13.250 0.7794 0.09471 0.08896 0.0292 0.0257 1.0000
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